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transcript
January 5, 2007
THEMIS Mission
Readiness Review
January 5, 2007 THEMIS Mission Readiness Review 2
Mission Overview
Mission Science/EPO
System Engineering
Integration & Test
Operations
Launch Day
Launch Vehicle Readiness
Safety & Mission Assurance
Software IV&V
Integrated Independent Review Team
Public Affair Plan
Readiness Statement
Frank Snow - Mission Manager
Vassilis Angelopoulos - PI
Peter Harvey - Project Manager
Peter Harvey - Project Manager
Peter Harvey - Project Manager
Frank Snow - Mission Manager
Garrett Skrobot Mission Integration Manager
Ronald Pierson - Explorer SAM
Judith Connelly - THEMIS IV&V
Mark Goans - IIRT Chair
Cynthia O’Carroll - GSFC PAO
Frank Snow – Mission Manager
Agenda
January 5, 2007 THEMIS Mission Readiness Review 3
Mission Overview
Frank Snow
Mission Manager
January 5, 2007 THEMIS Mission Readiness Review 4
Purpose
• To show the CMC all elements, both ground and flight, are ready to proceed to launch.
• CMC concur with the residual risks for the THEMIS project.
January 5, 2007 THEMIS Mission Readiness Review 5
Organization
Mission Manager Frank Snow, GSFC
Mission Manager Frank Snow, GSFC
Financial MgrK. Harps, UCBFinancial MgrK. Harps, UCB
Launch Vehicle G. Skrobott, KSC
Launch Vehicle G. Skrobott, KSC
Project Scientist D. Sibeck, GSFC
Project Scientist D. Sibeck, GSFC
THEMIS PI V. Angelopoulos, UCB
THEMIS PI V. Angelopoulos, UCB
Project Manager P. Harvey, UCB
Project Manager P. Harvey, UCB
Science Co-I’s Science Co-I’s EPO N. Craig, UCB
EPO N. Craig, UCB
SubcontractsJ. Keenan, UCBSubcontracts
J. Keenan, UCBScheduling
D. Meilhan, UCBScheduling
D. Meilhan, UCBQuality
AssuranceR. Jackson, UCB
Quality Assurance
R. Jackson, UCB
Mission Systems
E. Taylor, UCB
Mission Systems
E. Taylor, UCB
Mechanical/ Thermal Systems
P. Turin, UCBC. Smith, UCB
Mechanical/ Thermal Systems
P. Turin, UCBC. Smith, UCB
Mag Cleanliness
C. Russell, UCLA
Mag Cleanliness
C. Russell, UCLA
Probe/Probe CarrierManagement
UCB Oversight: D. KingSwales Mgr: M. Cully
Probe/Probe CarrierManagement
UCB Oversight: D. KingSwales Mgr: M. Cully
Instruments
P. Berg, UCB
Instruments
P. Berg, UCB
Operations
M. Bester, UCB
Operations
M. Bester, UCB
Software Systems
D. King, UCB
Software Systems
D. King, UCB
Mission I&T
J. McCauley, UCBR. Sterling, UCB
Mission I&T
J. McCauley, UCBR. Sterling, UCB
January 5, 2007 THEMIS Mission Readiness Review 6
TIME HISTORY OF EVENTS AND MACROSCALE
INTERACTIONS DURING SUBSTORMS (THEMIS)
RESOLVING THE PHYSICS OF ONSET AND EVOLUTION OF SUBSTORMS
Principal InvestigatorVassilis Angelopoulos, UCB
EPO LeadNahide Craig, UCB
Project ManagerPeter Harvey, UCB
Industrial PartnerSWALES Aerospace
SCIENCE GOALS:
Primary:
“How do substorms operate?”– One of the oldest and most important
questions in Geophysics– A turning point in our understanding
of the dynamic magnetosphere
First bonus science:
“What accelerates storm-time ‘killer’ electrons?”– A significant contribution to space weather science
Second bonus science:
“What controls efficiency of solar wind – magnetosphere coupling?”– Provides global context of
Solar Wind – Magnetosphere interaction
January 5, 2007 THEMIS Mission Readiness Review 7
LaunchVehicle: Delta II, Eastern RangeApogee: 91845.2 km ± 9567 kmPerigee: 435 km ± 10 km Inclination: 16.0 deg ± 0.5 degDate: February 15, 2007
Space SegmentSpacecraft: 5 Spinning Probes with Fuel for Orbit & Attitude
AdjustInstruments: 3-Axis Electric Field, Magnetic Field
3-D Ion & Electron Particle DetectorsSpin Rate: 20 RPMOrbit Period(s): 1, 2 and 4 daysOrientation: Ecliptic Normal
Ground SegmentObservatories: 20 Northern with All Sky Imagers and
MagnetometersControl Facilities: Mission and Science Operations Centers
OperationsPhases: L&EO, Cruise, Ascent, Campaigns, De-orbitLifetime:2.3 years
Mission Summary
January 5, 2007 THEMIS Mission Readiness Review 8
Instrument Configuration
IDPU: Instrument Data Processor UnitSPB : Spin Plane Booms (4x)AXB : Axial Booms (2x)SST : Solid State Telescope (2x)ESA : Electrostatic Analyzer FGM : Fluxgate MagnetometerSCM : Search Coil Magnetometer
January 5, 2007 THEMIS Mission Readiness Review 9
Fuel Tank
ESA
EFI SPB
Thruster T1
EFI Axial Booms (2, Stowed)
BatteryBAU
Repress Tank
Miniature Sun Sensor
Transponder
Thruster T2
IDPU
Fuel Tank
Antenna
EFI SPB
EFI SPB
Thruster A1
Thruster A2
AEB
Gyros
Probe Configuration
January 5, 2007 THEMIS Mission Readiness Review 10
Ground Based Observatories
Ground Based Observatories • UCB has Delivered All 20 GBO (GMAG and ASI) units• 19 Have Been Installed, 1 Needs Repair• Automatic Data Collection and Archiving in Progress• Remote Commanding and Diagnostics Working • Expect to be Fully Functional at Winter 2008
Courtesy H.Frey, UCB
GeographicLongitude 324°
Geographic Longitude 195°
GeomagneticNorth Pole
GeographicNorth Pole
January 5, 2007 THEMIS Mission Readiness Review 11
Ground Observatory Status
Unit # Location StatusGB0#02 Athabasca Operating normallyGB0#03 Prince George Down for Repair (/1)GB0#04 Ekati Diamond Mine Operating normallyGB0#06 The Pas Operating normallyGB0#07 Whitehorse Operating normallyGB0#08 Inuvik RF Interference (/2)GB0#09 Rankin Inlet RF Interference (/2)GB0#10 Fort Smith Operating normallyGB0#11 McGrath Operating normallyGB0#12 Fort Yukon Operating normallyGB0#13 Univ. of Calgary To Be Installed at NainGB0#14 Goose Bay RF Interference (/2)GB0#15 Kapuskasing Operating normallyGB0#16 Pinawa Operating normallyGB0#17 Chibougamau Operating normallyGB0#18 Gakona Operating normallyGB0#19 Gillam Operating normallyGB0#20 Kiana Operating normallyGB0#21 Ft. Simpson Operating normallyGB0#22 Sanikiluaq Operating normally
Ground Based ObservatoriesUnit # Location StatusGB0#02 Athabasca Operating normallyGB0#03 Prince George Down for Repair (/1)GB0#04 Ekati Diamond Mine Operating normallyGB0#06 The Pas Operating normallyGB0#07 Whitehorse Operating normallyGB0#08 Inuvik RF Interference (/2)GB0#09 Rankin Inlet RF Interference (/2)GB0#10 Fort Smith Operating normallyGB0#11 McGrath Operating normallyGB0#12 Fort Yukon Operating normallyGB0#13 Univ. of Calgary To Be Installed at NainGB0#14 Goose Bay RF Interference (/2)GB0#15 Kapuskasing Operating normallyGB0#16 Pinawa Operating normallyGB0#17 Chibougamau Operating normallyGB0#18 Gakona Operating normallyGB0#19 Gillam Operating normallyGB0#20 Kiana Operating normallyGB0#21 Ft. Simpson Operating normallyGB0#22 Sanikiluaq Operating normally
Ground Based Observatories
/1: Supply Down/2: Radar RF Noise
January 5, 2007 THEMIS Mission Readiness Review 12
Ground System Diagram
Ground System Elements•Ground Stations
•Ground Network
•Space Network
•Mission Operations Center
•Science Operations Center
•Flight Dynamics Center
Including•Mission Design
•Orbit & Attitude Determination
•Maneuver Planning
•Limit Detection and Notification
•Network Security
January 5, 2007 THEMIS Mission Readiness Review 13
Pictures from JPL
Environmental Testing
Probe Carrier Assembly during Vibration
Installation of Thermal Vacuum Shrouds
Probe on GSFC Spin Balance Miller Table
Two Probes Ready for TV Testing
January 5, 2007 THEMIS Mission Readiness Review 14
Probe Rollover Fixture in JPL Clean room
Probes in Storage, Ready for Launch Operations
Pictures from JPL
Environmental Testing
January 5, 2007 THEMIS Mission Readiness Review 15
THEMIS Probe Carrier Assembly (PCA) in Launch Configuration
Pictures from JPL
Environmental Testing
January 5, 2007 THEMIS Mission Readiness Review 16
Ground Stations
Ground StationStation
DesignatorFigure of
MeritLocation Function
Berkeley, CA BGS 11-m 24.0 dB/K37.879° N 122.243° W
Primary TLM/CMD/TRK
Wallops Island, VA WGS 11-m 23.0 dB/K37.925° N75.476° W
Secondary TLM/CMD/TRK
Merritt Island, FL MILA 9-m 1/2 21.6 dB/K28.508° N80.693° W
Secondary TLM/CMD/TRK
Santiago, Chile AGO 9-m 21.6 dB/K33.151° S70.668° W
Secondary TLM/CMD/TRK
Hartebeesthoek, SA HBK 10-m 20.4 dB/K25.883° S27.708° E
Secondary TLM/CMD/TRK
Mission Supported by 5 Ground Stations• Ground Stations: BGS, WGS, MILA, AGO, HBK• GN, SN and FDF Support Documented in PSLA• All Stations Have Successfully Flowed Data with MOC
January 5, 2007 THEMIS Mission Readiness Review 17
Contacts - TDRSS
TDRSS Contact Summary• Launch Support
– Monitoring of Probe A Separation
• Maneuver Support Near Perigee for All Probes– Apogee Change for Mission Orbit Placement – Initiation of Reentry
• Contingency Support for All Probes– Only Few TDRSS Contingency Support Hours Required
ProbeTDRSS Support
Launch Maneuver Contingency
1 1 h 19 h 2
2 19 h 2
3 2 h 2
4 2 h 2
5 5 h 2
Subtotal 1 h 47 h 10 h
Total Support 58 h
January 5, 2007 THEMIS Mission Readiness Review 18
Launch Vehicle Overview• Vehicle Configuration: Delta 7925–10C• Launch Site: Eastern Range (ER), SLC-17B at
Cape Canaveral Air Force Station (CCAFS)• Mission Specifics:
– Perigee: 435 km, Apogee: 91845 km– Orbit Inclination: 16 degrees– Spacecraft (SC) Mass (will not exceed)
» 829 kg (2832.94lb) 775.60 kg actual– STAR 48B Motor
» Nutation Control System» Yo-Yo de-spin system
• Spin rates: – During Third Stage operation - max 70 rpm– S/C after spin-down and separation - 162 rpm
• Mission Unique– 3712 Bolted PAF– Sep System (at PAF/PC Interface)
• Non-Standard Services– Category 1 Analysis
» (1st 7925-10C ER)– Five - 24” Doors– Two 61 pin connectors– Fairing Cleaning to VC 6
• Separation System provided by THEMIS Spacecraft, contracted through Launch Services Program (LSP)NASA Launch Service (NLS) Contract
January 5, 2007 THEMIS Mission Readiness Review 19
Mission Parameters
• Launch Period 15 February 07 – 14 March
07
• Daily Launch Opportunities
–Single flight azimuth/SECO 1 trajectory 93 Deg
–Single Second Stage restart/Third Stage trajectories
–Window Duration 19.6 min• Launch period has been divided into two blocks of dates Opening
15 February to 28 February 23:08:00 UTC (Changes by 3:34
per day)
01 March to 14 March 21:57:00 UTC (Changes by 3:34 per day)
–Liftoff times are rounded to the nearest whole minute
–Mission Assurance Collision Avoidance (COLA) Measures will be accomplished
• Free Molecular Heating Rate at Fairing Separation < 0.1 BTU/ft2/sec
• Sun Angle Constraints: Centerline during coast 90 +/- 9 deg
January 5, 2007 THEMIS Mission Readiness Review 20
Depletion Burn:Removes Stage 2 fromvicinity of spacecraft,while lowering Stage 2 perigee altitude andorbit inclination
Flight Profile
Liftoff
MECOt = 263.3 secAlt = 69.0 nmiVI = 20,060 fps
Second Stage Ignitiont = 276.8 secAlt = 72.9 nmiVI = 20,068 fps
Fairing Jettisont = 281.0 secAlt = 74.1 nmiVI = 20,103 fps
SECO 1t = 593.5 secAlt = 101.9 nmiVI = 25,923 fps
ORBIT:100 x 304 nmi28.50 deg inclination
Second Stage Restartt = 3859.4 secAlt = 282.7 nmiVI = 24,662 fps
SECO 2t = 3915.1 secAlt = 280.6 nmiVI = 25,778 fps
ORBIT:280 x 825 nmi26.58 deg inclination
TECOt = 4091.6 secAlt = 305.2 nmiVI = 33,975 fps
Separate Probe At = 4380.1 secAlt = 658.6 nmiVI = 32,368 fps
Orbit:235 x 49,592 nmi16.00 deg inclination-40.00 deg arg of per
SRM Impact SRM Impact
SRM Jettison (6)t = 66.0 / 67.0 secAlt = 9.9 / 10.2 nmiVI = 3,231 / 3,269 fps
SRM Jettison (3)t = 131.5 secAlt = 31.3 nmiVI = 8,018 fps
Third Stage Ignitiont = 4005.1 secAlt = 281.0 nmiVI = 25,775 fps
Note: Values shown are for 15-28 Feb 2007 launch
January 5, 2007 THEMIS Mission Readiness Review 21
Integration Flow
Probe Fueling Probe RCS Electr. Verif.
Weigh Wet Probes, Attach Pyro
PCA Funct.Spin Balance
PCA Comm Check @ Blockhouse
Install Pyro Signal SMDC/ Weigh PCA
Engr Walk-down/ Trans- port Preps
Move Probes to HPF
Weigh PCA
PCA Mate to 3rd Stage/ Clamp-band Instl
Transport to Pad
S/C Functional & RF Test
Launch Rehearsal
Power On & Stray Voltage
Install Fairing
Prop. Load Prep
2nd Stage Fueling, Ordnance
Launch Readiness Review
La
un
ch
Sh
ipp
ing
fr
om
JP
L 12/08/06
12/21/06
02/02/07
02/15/0702/14/07
ASTROTECH and Launch Pad Flow
12/11/06 12/12/06
01/08/07
01/15/07
01/13/0701/05/0712/22/06
12/13/06
02/03/07 02/05/07 02/12/07 02/13/07
PCA Functional
01/23/0701/22/07
12/23/06 01/02/07
Reserve
Christmas Shutdown
12/11/06to
12/18/06
12/19/06
12/15/06
12/11/06
THEMIS Launch
01/03/07
02/07/0702/06/07
12/15/0612/14/06 12/19/0612/15/06 12/20/0612/19/06
5 Probes plus EGSE, MGSE at ASO
Probe Carrier Unpack
Unpack, Setup EGSE
PC-VCO Electrical Test
Install Sep. Harness
Install SMDC Lines
F1 RCS MEOP, LPT, S/A Test
Install Bolt Cutters, Therm. Closeouts
F2-3 RCS MEOP, LPT, S/A Test
F4-5 RCS MEOP, LPT, S/A Test
Weigh, Move to Stands
Pre-VosMRR (GSFC)
01/0301/05
LVRR (KSC) 01/12
Media Day 01/12
01/09/07 01/10/07 01/11/07 01/12/07
MRR (HQ) 01/23
01/24/07 01/25/07 01/26/07 01/27/07 01/29/07 01/30/07
LSRR (CCAFS) 02/01
01/3107 02/01/07
02/09/0702/08/07
LMCM (KSC) 02/13FRR (KSC) 02/12
January 5, 2007 THEMIS Mission Readiness Review 21
January 5, 2007 THEMIS Mission Readiness Review 22
Milestones/Reviews
• NASA funds THEMIS proposal/concept study March, 2003
• Confirmation Review May 2004
• Cost Credibility Review June 2005
• Mission Readiness Review January 2007
• 27 IIRT Reviews
• Peer Reviews, Code 500 schedule reviews, Explorer Program Mission Analysis Reviews (before MOR and FOR), code 500 BAU Review team.
Key Reviews
• Safety/Mission Assurance Review 1/19/07• Mission Readiness Board 1/23/07• Flight Readiness Review 2/12/07• Launch Readiness Review 2/14/07
January 5, 2007 THEMIS Mission Readiness Review 23
Integrated Independent Review Team (IIRT) Members
–Mark Goans GSFC [Systems Review Office] (Co-chair)–Brian Keegan Independent (Co-chair)–Bill Taylor Independent - Project Mgt., Systems–Frank Martin Independent - Science, Instruments–J. B. Joyce Independent - Operations–Terry Ford Independent - GN & C–Rick Schnurr GSFC - Electrical Systems–Alan Posey GSFC - Mechanical Systems–Lou Fantano GSFC- Thermal –Scott Glubke GSFC - Propulsion–Ed Gaddy GSFC - Power–Ronnie Killough SWRI - Software
January 5, 2007 THEMIS Mission Readiness Review 24
Explorer Program Champion Team
–John Deily 590 - Assoc. Division Chief, Champion Team Chair
–Rick Schnurr 560 - Chief Electrical Systems Architect
–Tom McCarthy 500 - AETD Chief Engineer
–Ken Hinkle 540 Division Chief
–John Leon 556 Branch Head
–John Donohue 580 Assoc. Division Chief
24
January 5, 2007 THEMIS Mission Readiness Review 25
Mission Science/EPO
Vassilis Angelopoulos
Principal Investigator
Mission Science Overview and Investigation Strategy
Science Team Preparations and Readiness
Full and Minimum Science Criteria
EPO
January 5, 2007 THEMIS Mission Readiness Review 26
TIME HISTORY OF EVENTS AND MACROSCALE
INTERACTIONS DURING SUBSTORMS (THEMIS)
RESOLVING THE PHYSICS OF ONSET AND EVOLUTION OF SUBSTORMS
Principal InvestigatorVassilis Angelopoulos, UCB
EPO LeadNahide Craig, UCB
Project ManagerPeter Harvey, UCB
Industrial PartnerSWALES Aerospace
SCIENCE GOALS:
Primary:
“How do substorms operate?”– One of the oldest and most important
questions in Geophysics– A turning point in our understanding
of the dynamic magnetosphere
First bonus science:
“What accelerates storm-time ‘killer’ electrons?”– A significant contribution to space weather science
Second bonus science:
“What controls efficiency of solar wind – magnetosphere coupling?”– Provides global context of
Solar Wind – Magnetosphere interaction
January 5, 2007 THEMIS Mission Readiness Review 27
Auroral Eruptions and Substorms
Auroral eruptions…
AuroraAurora
…are a manifestation ofmagnetospheric substorms
MAGNETOSPHERESO
LAR
WIN
D
EQUATORIAL PLANE
January 5, 2007 THEMIS Mission Readiness Review 28
Mission ElementsProbe conjunctions along Sun-Earth line recur once per 4 days over North America.
Ground based observatories completely cover North American sector; can
determine auroral breakup within 1-5s …
… while THEMIS’s space-based probes determine onset of Current Disruption and Reconnection each
within <10s.
: Ground Based Observatory
January 5, 2007 THEMIS Mission Readiness Review 29
First bonus: What producesstorm-time “killer” MeV electrons?
Affect satellites and humans in space
Source:
– Radially inward diffusion?
– Wave acceleration at radiation belt?
THEMIS:
–Tracks radial motion of electrons
•Measures source and diffusion
•Frequent crossings
–Measures E, B waves locally
ANIK telecommunicationsatellites lost for days to weeks
during space storm
January 5, 2007 THEMIS Mission Readiness Review 30
Second bonus: What controls efficiencyof solar wind – magnetosphere coupling?
Important for solar wind energy transfer in Geospace
Need to determine how:– Localized pristine solar wind features…– …interact with magnetosphere
THEMIS:
– Alignments track evolution of solar wind
– Inner probes determine entry type/size
January 5, 2007 THEMIS Mission Readiness Review 31
THEMIS is firmly aligned withNASA’s Vision for Space Exploration
…To Explore Earth-Sun System and understand effects on Earth and implications for human exploration [Strategic Roadmap #10 of Exploration Initiative]
• Radiation hazards pose a risk to spacecraft and humans in Earth orbit and en-route to Mars • Radiation is caused by solar energetic particles and galactic cosmic rays, and radiation belts• Nowhere else can the understanding of the underlying physics of particle acceleration more
comprehensive, detailed and complete than at and around Earth’s vicinity.
Exploration building blocks:• Understand processes of particle acceleration at Earth and in solar wind• Understand interactions between solar wind and planetary magnetospheres• Understand how harmful particle populations develop and evolve • Predict conditions and implications of radiation for human exploration
THEMIS is a critical element of the ESS Exploration agenda:• Addresses how fundamental particle acceleration processes operate
- First comprehensive, coordinated measurements of energy sources and sinks
• Tracks energetic particles from seed to target
- Probe conjunctions strategically designed to answer this question
January 5, 2007 THEMIS Mission Readiness Review 32
Science ObjectivesTHEMIS HAS FOCUSED MINIMUM (TO BASELINE) OBJECTIVES:
• Time History of Events…– Auroral breakup (on the ground)– Current Disruption [CD] (2 probes at ~10RE) – Reconnection [Rx] (2 probes at ~20-30RE)
… and Macroscale Interactions during >5 (>10) Substorms (Primary):– Current Disruption and Reconnection coupling
• Outward motion (1600km/s) of rarefaction wave • Inward motion of flows (1000km/s) and Poynting flux.
– Ionospheric coupling• Cross-tail current reduction (P5u/P4) vs flows• Field aligned current generation by flow vorticity, pressure gradients (P/dz, P/dx).
– Cross-scale coupling to local modes• Field line resonances (10RE, 5 min)
• Ballooning modes, KH waves (1RE, 1min)
• Weibel instability, cross-field current instability, kinetic Alfven waves (0.1RE, 60Hz)
• Production of storm time MeV electrons (Secondary)
• Control of solar wind-magnetosphere coupling by the bow-shock, magnetosheath and magnetopause (Tertiary)
January 5, 2007 THEMIS Mission Readiness Review 33
Probe Conjunction Requirements
BASELINE: >10 substorms per year for 2 tail seasons (188hrs / tail season)
MINIMUM: >5 substorms in 1yr w/ 4 probes in 1 tail season (94hrs total).
– YP1/2/3/4/5<±2RE; ZP3,4,5/NS<±2RE; ZP1,2/NS<±5RE
Actual conjunction times in 1st year
Science orbits P1 P2 P3 P4 P5Period (days) 4 2Apogee (RE) 30 19 12 12 12
Perigee (RE) 1.5 1.2
Inc @ midtail
Drift @ apg., @6:30UT
Knowledge @ apg.
Y<1RE/month
100 km
1
1.16
~7o ~9o
Prime Science: Feb 15+/- 1.5 mo:– Between Winter Solstice and Equinox– A compromise: Shadows vs Conjunctions
Launch Delay (Oct 19 ’06 to Feb 15 ‘07) effects:– Baseline science yield and quality are still nominal– Adds an 8mo. coast phase ahead of 1st tail season– Probes assigned positions early, placements after coast phase
Avoids differential precession P2,3,4 deploy EFIs vs. P1,5 keep EFIs stowed for placements
Compromise: ease of placement vs. early science
January 5, 2007 THEMIS Mission Readiness Review 34
Probe Conjunctions Satisfied
Launch day analysis:Feb 15 to May 15, 2007Conjunctions are robust
Nominal deltaV marginfor operations at launch:>25% for baseline mission>15% for replacement probe
Conjunction Hours Expected:>25% margin above baseline>150% margin by 1st Tail Season
Tail 1
Dayside
Tail 2
Baseline Requirement
Minimum Requirement
Baseline Requirement
Baseline Requirement
January 5, 2007 THEMIS Mission Readiness Review 35
SST
ESA
EFIa
EFIs
FGM
SCM
Tspin=3s
1 FGM: Low freq. B-field (0-64Hz)1 ESA: Thermal plasma2 SSTh (heads): Super-thermal plasma1 SCM: High freq. B-field (1Hz-4kHz)4 EFIs (spin plane) &2 EFIa (axials): Low&High freq. E-field
Instruments Required:Redundancy and Overlap
Instruments required for Primary Mission Objective (Substorms)
Measurement goals P1 P2 P3 P4 P5Tim
e History of E
vents
P3,4&5 monitor CDP1,2 bracket Rxtres<30s, Y<±2RE
FGM
1SSTh
2EFIs
FGM
ESA
2SSTh
2EFIs
FGM
ESA
1SSTh
FGM
ESA
1SSTh
FGM
ESA
1SSTh
Macroscale Interactions
Track rarefaction wave, inward flows, Poynting with B<1nT, V/V~10%
FGM
ESA
FGM
ESA
FGM
ESA
FGM
ESA
Radial/cross-sheet pressure, velocity and current gradients require P/P~ V/V ~ B/B ~10%, non-MHD
FGM
ESA
FGM
ESA
2EFIs
FGM
ESA
2EFIs
FGM
ESA
2EFIs
Cross-tail pairs measure FLRs, KH, ballooning on B, V, P @ 10s and fast modes on Bxyz and Exy @ 60 Hz
FGMESA SCM
FGMESA
SCM 4EFIs2EFIa
FGM
ESA
2EFIs
FGM
ESA
SCM 4EFIs2EFIa
SU
MM
AR
Y
Minimum mission (Red)
Baseline add-ons (green)
FGM
1SSTh
2EFIs
FGM
ESA
2SSTh
SCM2EFIs
FGM
ESA
1SSTh
SCM 4EFIs2EFIa
FGM
ESA
1SSTh
2EFIs
FGM
ESA
1SSTh
SCM 4EFIs2EFIa
January 5, 2007 THEMIS Mission Readiness Review 36
Baseline L1 Requirements
• S-1 Substorm Onset Time– Determine substorm onset time and substorm meridian magnetic local time (MLT) using ground ASIs (one per
MLT hr) and MAGs (two per MLT hr) with t_res<30s and dMLT<1 degree respectively, in an 8hr geographic local time sector including the US. (M-11, GB-1)
• S-2 Current Disruption (CD) Onset Time– Determine CD onset time with t_res<30s, using two near-equatorial (within 2Re of magnetic equator) probes,
near the anticipated current disruption site (~8-10 Re). CD onset is determined by remote sensing the expansion of the heated plasma via superthermal ion flux measurements at probes within +/-2Re of the measured substorm meridian and the anticipated altitude of the CD. (M-9, IN.SST-1, IN.SST-4, IN.FGM-1)
• S-3 Reconnection (Rx) Onset Time– Determine Rx onset time with t_res<30s, using two near-equatorial (< 5Re from magnetic equator) probes,
bracketing the anticipated Rx site (20-25Re). Rx onset is determined by measuring the time of arrival of superthermal ions and electrons from the Rx site, within dY=+/-2Re of the substorm meridian and within <10Re from the Rx altitude. ….. (M-9, IN.EFI-2, IN.ESA-1, IN.SST-2, IN.SST-3, IN.SST-4, IN.FGM-1)
• S-4 Simultaneous Observations– Obtain simultaneous observations of: substorm onset and meridian (ground), CD onset and Rx onset for >10
substorms in the prime observation season (September-April). Given an average 3.75hr substorm recurrence in the target tail season, a 2Re width of the substorm meridian, a 1Re requirement on probe proximity to the substorm meridian (of width 2Re) and a 20Re width of the tail in which substorms can occur, this translates to a yield of 1 useful substorm event per 18.75hrs of probe alignments, i.e, a requirement of >188hrs of four-probe alignments within dY=+/-2Re. (M-1, M-12, IN.FGM-1)
January 5, 2007 THEMIS Mission Readiness Review 37
• S-5 Earthward Flows– Track between probes the earthward ion flows from the Rx site and the tailward moving rarefaction wave in
the magnetic field, and ion plasma pressure with sufficient precision to ascertain macroscale coupling between current disruption and reconnection site during >10 substorm onsets (>188hrs of four-probes aligned within dY of +-2Re). (IN.ESA-1, IN.SST-3, IN.FGM-1)
• S-6 Pressure Gradients– Determine the radial and cross-current-sheet pressure gradients and ion flow vorticity/deceleration with
probe measurement accuracy of 50km/s/Re, over typical inter-probe conjunctions in dR and dZ of 1Re, each during >10 onsets. (IN.EFI-1, IN.ESA-1, IN.ESA-2, IN.SST-3, IN.FGM-1)
• S-7 Cross-Current Sheet changes– Determine the cross-current-sheet current change near the current disruption region (+/-2Re of meridian, +-
2Re of measured current disruption region) at substorm onset from a pair of Z-separated probes using the planar current sheet approximation with relative (interprobe) resolution and inter-orbit (~12hrs) stability of 0.2nT. (IN.FGM-1, PB-42, PB-43, PB-44)
• S-8 non-MHD plasma– Obtain measurements of the Magneto-Hydrodynamic (MHD) and non-MHD parts of the plasma flow
through comparisons of ion flow from the ESA detector and ExB flow from the electric field instrument, at the probes near the current disruption region, with t_res<10s. (IN.EFI-1, IN.ESA-1, IN.SST-3, IN.FGM-1)
… continued: Baseline L1 Requirements
January 5, 2007 THEMIS Mission Readiness Review 38
• S-9 Cross-Tail Pairs– Determine the presence, amplitude, and wavelength of field-line resonances, Kelvin-Helmholz waves and
ballooning waves on cross-tail pairs (dY=0.5-10Re) with t_res<10s measurements of B, P and V for >10 substorm onsets. (IN.ESA-1, IN.SST-3)
• S-10 Cross-Field Current Instabilities– Determine the presence of cross-field current instabilities (1-60Hz), whistlers and other high frequency
modes (up to 600Hz) in 3D electric and magnetic field data on two individual probes near the current disruption region for >10 substorm events. (IN.EFI-3, IN.ESA-3, IN.SCM-1)
• S-11 Dayside Science– Determine the source and acceleration mechanism of storm-time MeV electrons at the radiation belts by
measuring the radial evolution of the electron phase space density over time-scales of 2-6 hrs. (IN.ESA-4, IN.SST-6)
• S-12 Dayside Science– Determine the nature, extent and cause of magnetopause transient events via comparing simultaneous
measurements of the dynamic pressure in the pristine solar wind and the foreshock with magnetic field perturbations near the magnetopause. (IN.ESA-4, IN.SST-6)
… continued: Baseline L1 Requirements
January 5, 2007 THEMIS Mission Readiness Review 39
Minimum L1 Requirements (from L1’s)
• 4.1.2.1 Substorm Onset Time– Determine substorm onset time and substorm meridian magnetic local time (MLT) using ground MAGs (at
least one per MLT hr) with t_res<30s and dMLT<6 degrees respectively, in a 6hr geographic local time sector including the US.
• 4.1.2.2 Current Disruption (CD) Onset Time– Determine CD onset time with t_res<30s, using two near-equatorial (within 2Re of magnetic equator)
probes, near the anticipated CD site (~8-10 Re). …(same as baseline)
• 4.1.2.3 Reconnection (Rx) Onset Time– Determine Rx onset time with t_res<30s, using two near-equatorial (<5Re of magnetic equator) probes,
bracketing the anticipated Rx site (20-25Re). … (same as baseline)
• 4.1.2.4 Simultaneous Observations– Obtain simultaneous observations of: substorm onset and meridian (ground), CD onset and reconnection
onset for >5 substorms in the prime observation season (September-April). Substorm statistics discussed in S-4 point to a requirement of >94hrs of four probe alignments.
• 4.1.2.5 Earthward Flows– Track between probes the earthward ion flows from the reconnection site and the tailward moving rarefaction
wave in the magnetic field, and ion plasma pressure with sufficient precision precision to ascertain macroscale coupling between current disruption and reconnection site during >5 substorm onsets.
January 5, 2007 THEMIS Mission Readiness Review 40
Science Team Composition
• Added Strength w/ 5 new coIs:– J. Bonnell (EFI)
– D. Larson (SST)
– J. P. McFadden (ESA)
– I. Mann (UoA GBO, RadBelt)
– I. Daglis (Athens, Ring Current)
• Established Partnerships with:– Taiwan [Affiliate F. Cheng]
– Cluster [Affiliate S. Schwarz]
– SPDF [Affiliate R. McGuire]
– CCMC [Affiliate M. Hesse]
• Enlisted young bright stars:– Chaston, Eastwood, Hull, Keiling
(UCB), Strangeway, Schwarzl, Weygand (UCLA)
• Team is ready, awaiting launch!
January 5, 2007 THEMIS Mission Readiness Review 41
Science Team Meetings and Products
• Meetings• Yearly post-AGU meetings at UCB since 2003
• “Data analysis tools” meeting at UCB, Nov-15-2006
– Exposed team to (and obtain feedback on) data analysis tools before they are finalized coast phase intra-calibration and unique science
• Weekly Science and Science Ops Center Development meetings
• Weekly International Instruments telecons (FGM, SCM, ASIs)
• Cape Canaveral Feb 13-15 meeting announced (Team+Community)
• Call for Space Science Reviews instrument papers to be submitted– Expect comprehensive volume by next summer, out well before for Tail 1:
» Analysis tools and methods» First instrument results
• Web page development:– Contracted analysis tools and data dissemination web-site
– Brainstorming team and Contractor interfaces established
– Skeleton and content material in place in beta site
– User interviews on-going to establish best look and feel.
January 5, 2007 THEMIS Mission Readiness Review 42
Science Data Products Status
Level 0 Data : Raw files (*.pkt) one per APID (application identifier, straight from telemetry).
Level 1 Data : Processed but uncalibrated data in CDF (Common Data Format) files (*.cdf)
Software and calibration files will be distributed with the data.
Level 2 Data: Calibrated data in CDF files – contain physical quantities.
January 5, 2007 THEMIS Mission Readiness Review 43
Science Team Data Analysis Tools Status (1)
• Analysis tools available now (IDL-based) at:http://themis.ssl.berkeley.edu/beta
– Platform independent, works on Solaris, Linux, Win, MacOSx
– Auto file retrieval
– Easy to install and download files
– GUI available for IDL starters
• Contributions by any scientist
• Maintenance with SubVersioN
• Documentation includes:
– Users Guide
– Developers Guide
– Subversion
– Latest list of routines
January 5, 2007 THEMIS Mission Readiness Review 44
Science Team Data Analysis Tools Status (2)
• Anyone can plot L1 data from THEMIS today:http://themis.ssl.berkeley.edu
– Data from I&T period, is auto-processed whenever software is updated
– Working on mirror sites
– Additional plots at SPDF:
– via CDAWweb
January 5, 2007 THEMIS Mission Readiness Review 45
Science Team Data Analysis Tools Status (3)
• Orbit Visualization, conjunction searches and footpoints:http://sscweb.gsfc.nasa.gov/ Thanks to excellent support from SPDF!
– Orbit visualization via “tipsod”: a Java – based software
January 5, 2007 THEMIS Mission Readiness Review 46
Web-based L2 overview plot distribution (4)
http://themis.ssl.berkeley.edu/summary_plots/plot_display.php
January 5, 2007 THEMIS Mission Readiness Review 47
Science Readiness Summary
• Science Team In Place, Eagerly Awaiting Launch
• L0, L1 Automated Science Data Processing In Place
• L1 Data Analysis Tools Available for Team and Public
• L2 Data Production Routines Based on Past Missions, under construction (Expected before launch)
• Web-based Plots, Data and Tools Dissemination in Place– Using I&T data for testing
• System in Place for Software Contributions
• L2 Data Readily Accessible by SPDF and Cluster– ISTP compatible
– Self-documented and readable by QSAS
January 5, 2007 THEMIS Mission Readiness Review 48
• Started yearly teacher workshop site in Carson City, NV in collaboration with LHS
– Workshops held in June ’05 and June ‘06
• Installed 13 magnetometers and involved teachers to test lesson plans
• Developed, tested & revised Magnetism on Earth teacher’s guide, used now in classrooms
• Real-time data on the web
• Archived data available on the web
UCB Carson City NV
Bay Mills College
THEMIS EPO Program
January 5, 2007 THEMIS Mission Readiness Review 49
Overview– Magnetometers in 13 schools in 10 states– 14+ teachers involved– Teachers leaving mirror lessons at next place
• Teacher turnaroud has multiplication effect
– Data on the web– Mostly high school classes– Students excited by wiggles and spectrograms– Student research
• AGU presentations by students
Magnetometer Data at Schools
January 5, 2007 THEMIS Mission Readiness Review 50
• Background science lessons – Exploring Magnetism and Magnetism on Earth
teacher guides– Space Science Weekly Problem
• Using data in the classroom– Correlations of magnetism data with other space
weather data– Soda bottle Magnetometer comparison to
research-grade school magnetometer
• Working with Teachers– Maryland Science Center “Teacher’s Thursdays”
featured: “Exploring Magnetis Storms and Space Weather with THEMIS”exposing Educator Groups to THEMISAudience: ~30 present, 15 videoconferencing
– GEONS Workshops– Local Schools when invited
• Leveraging Other activities– THEMIS/GLOBE Workshops, Bay Mills, MI– Mission Observatory, AK– Michigan Science Teacher Association Workshops– Connections with STEREO and RHESSI– Connections with FAST
Education Activities Examples
January 5, 2007 THEMIS Mission Readiness Review 51
Public Outreach Examples
SAWANO NEWS (WI), Feb-2006
January 5, 2007 THEMIS Mission Readiness Review 52
Systems Engineering
Peter Harvey
Project Manager
January 5, 2007 THEMIS Mission Readiness Review 53
Design• Mission Description• Instrument and Probe Configuration• Launch and Mission Description
Requirements Verification• Summary, Waived and Pending Requirements• New Mission Profile Review• Resources• Operating Hours
Problem Failure Reports • Statistics and Status• Unverifiable Failures• Operational WorkArounds
Systems Agenda
January 5, 2007 THEMIS Mission Readiness Review 54
LaunchVehicle: Delta II, Eastern RangeApogee: 91845.2 km ± 9567 kmPerigee: 435 km ± 10 km (500 km ± 7 km on or after
3/1/2007)Inclination: 16.0 deg ± 0.5 degDate: February 15, 2007
Space SegmentSpacecraft: 5 Spinning Probes with Fuel for Orbit & Attitude
AdjustInstruments: 3-Axis Electric Field, Magnetic Field
3-D Ion & Electron Particle DetectorsSpin Rate: 20 RPMOrbit Period(s): 1, 2 and 4 daysOrientation: Ecliptic Normal
Ground SegmentObservatories: 20 Northern with All Sky Imagers and
MagnetometersControl Facilities: Mission and Science Operations Centers
OperationsPhases: L&EO, Cruise, Ascent, Campaigns, De-orbitLifetime: 2.3 years
Mission Summary
January 5, 2007 THEMIS Mission Readiness Review 55
Instrument Configuration
IDPU: Instrument Data Processor UnitSPB : Spin Plane Booms (4x)AXB : Axial Booms (2x)SST : Solid State Telescope (2x)ESA : Electrostatic Analyzer FGM : Fluxgate MagnetometerSCM : Search Coil Magnetometer
January 5, 2007 THEMIS Mission Readiness Review 56
Fuel Tank
ESA
EFI SPB
Thruster T1
EFI Axial Booms (2, Stowed)
BatteryBAU
Repress Tank
Miniature Sun Sensor
Transponder
Thruster T2
IDPU
Fuel Tank
Antenna
EFI SPB
EFI SPB
Thruster A1
Thruster A2
AEB
Gyros
Probe Configuration
January 5, 2007 THEMIS Mission Readiness Review 57
Standard Delta 10 ft. Fairing Static Envelope
3712 PAF
Probe Carrier Assembly (PCA = 5 Probes + Probe Carrier) on L/V
Probe Carrier Assembly (PCA = 5 Probes + Probe Carrier) on L/V
THEMIS Launch Configuration
THEMIS Launch Configuration
Probe Carrier Assembly (PCA) on Delta 3rd StageProbe Carrier Assembly (PCA) on Delta 3rd Stage
Launch ConfigurationDedicated launch
accommodated within standard Delta 7925-10 vehicle configuration and services
10’ Composite Fairing required to accommodate five Probes on the Probe Carrier in the “Wedding Cake” configuration
PC stays attached to Delta 3rd stage after probe dispense
Each probe dispense from the PCA is coordinated with but independent of the other probes
No single probe anomaly precludes dispense of remaining probes
Star 48 3rd Stage
January 5, 2007 THEMIS Mission Readiness Review 58
Mission Profile
January 5, 2007 THEMIS Mission Readiness Review 59
Mission Requirements Documentation (MRD)
• THM_SYS_001K_MRD.xls
Mission Requirements Verification
• 476 Requirements total
• 467 Requirements verified
• 5 Requirements pending
• 4 Requirements waived
Requirements Status
January 5, 2007 THEMIS Mission Readiness Review 60
Implementation Change
• IN.ESA-08: ESA Dayside Energy Flux Attenuator
Waived: Electronic Counting Was Fast Enough
• IN.DPU-09: Stored Housekeeping Telemetry Storage
Waived: BAU saves all IDPU Engineering Data
As Measured
• IN.EFI-11: EFI Noise Level < 1 x 10^-4 mV/m/sqrt(Hz).
Waived: EFI measured noise level is 2 to 3 x 10^-4 mVm/sqrt(Hz).
• PC.Mech-1: Probe-to-Probe Static Clearance of 4 inches
Waived: Current static clearance is 3.75 inches.
Requirements Waived
January 5, 2007 THEMIS Mission Readiness Review 61
Launch Site Verification
• M-33 Electrostatic Cleanliness requirement verification pending ESC survey after all flight close-outs (Jan 9)
• M-45, M-47, PC-8 PCA Mass Properties (Mass, CG, and Principle Misalignment) requirement verification pending PCA Spin Balance Test and final weighing of PCA with fueled Probes. (Jan 12 and 13)
Post-Launch Verification
• IN.ESA-13 ESA On-Orbit Calibration requires raw data to be collected prior to final coefficients to be delivered to the Science Operations Center. (March 2007)
Requirements Pending
January 5, 2007 THEMIS Mission Readiness Review 62
Mission Profile Review for Feb 15, 2007 Launch• EFI Boom Deploy delayed ~ 9 months on Probes 1 & 5
– THEMIS Deployment Motors Life Test (21 mo @ 50 C)– CLUSTER lifetime tests also relevant and showed no issues
• RCS Re-pressurization delayed about 6 months – No Issues with RCS Components– Cassini waited several years to do the recharge.
• Ascent Maneuvers Delayed appx 6 months– Increased IRU radiation qualification to 63 Krad (RDM of 2)
• Power considerations– Improved launch orientation, side solar arrays in sun.– No change in number or duration of eclipses
• Thermal environment– No change
New Mission Profile
January 5, 2007 THEMIS Mission Readiness Review 63
Mass Status
• < 2% mass deviation between Probes (requirement)• Dry Mass Margin: 4.5% (Worst case)
Power Status• Probe CBE: 38.7 W• Probe Capability: 40.60 W• Probe Margin: 8.8% (First 3-hour Eclipse Season)
4.9% (Second 3- hour Eclipse Season)
Resources
Mass(Kg) F1 F2 F3 F4 F5Measured 78.04 77.62 76.72 76.72 78.08NTE 81.80 81.80 81.80 81.80 81.80Margin 3.76 4.18 5.08 5.08 3.72% 4.6% 5.1% 6.2% 6.2% 4.5%
January 5, 2007 THEMIS Mission Readiness Review 64
Integrated Probe Hours:
Components : Averaged 780 hours run time prior to integration.
Failure Free Hours: Hours accumulated on core system after return of transponder and BAU during mission integration.
Late Instrument Swaps (>100 hours gained on integrated system after all swaps): • Spare SST on F1 swapped in prior to TVac in August• Spare SCM on F1 swapped in early October• EFI re-work on F1-F5 completed in November
Thermal Vacuum Hours: 120-150 failure free hours were accumulated on all components during Probe Level TVac. Components accumulated and average of 250 hours during Component Level TVac.
Operating Hours
0
50
100
150
200
250
300
350
400
450
500
Hours Failure Free
F1
F2
F3
F4
F5
January 5, 2007 THEMIS Mission Readiness Review 65
PFR Statistics (All Spacecraft)
• Total : 237
• Closed : 237
• Open : 0
• Unverifiable Failures : 13
• Operational Work-Arounds : 10
Problem/Failure Reports
January 5, 2007 THEMIS Mission Readiness Review 66
Unverifiable Failures
PFR # Problem Description Highest Probability AssessmentPFR 039 FGM Telem Errors Memory Configuration LOW: Temporary Data LossPFR 062 EFI V1 Signal Loss Sphere Grounded in Chassis LOW: Non-Flight ConfigurationPFR 070 IDPU Command Loss DMA Channel Issue LOW: Hardware ModifiedPFR 074 SST Chan 2 Data Loss FPGA Low Voltage. LOW: Hardware ModifiedPFR 108 EEPROM Load Error Writing too fast. LOW: Procedure ModifiedPFR 121 IDPU ETU Current over
specMis-measurement LOW: Minimal Current
PFR 130 BAU corrupting IDPU cmds IDPU DMA Channel Issue LOW: Hardware Modified
PFR 131 BAU corrupting IDPU cmds IDPU DMA Channel Issue LOW: Hardware Modified
PFR 147 BAU reset Break-out configuration MED: Operational complexity
PFR 161 Receiver lock prior to vib JPL Local transmitter LOW: No commands receivedPFR 172 K1 Battery Relay flipped GSE initial turn-on LOW: Only affected monitorSAI 0215 BAU reset and cmd loss GSE Power supply too low LOW: Non-Flight Configuration
SAI 0340 Thruster stops out of range. ITOS timing error LOW: Non-Flight Configuration
PFR # Problem Description Highest Probability AssessmentPFR 039 FGM Telem Errors Memory Configuration LOW: Temporary Data LossPFR 062 EFI V1 Signal Loss Sphere Grounded in Chassis LOW: Non-Flight ConfigurationPFR 070 IDPU Command Loss DMA Channel Issue LOW: Hardware ModifiedPFR 074 SST Chan 2 Data Loss FPGA Low Voltage. LOW: Hardware ModifiedPFR 108 EEPROM Load Error Writing too fast. LOW: Procedure ModifiedPFR 121 IDPU ETU Current over
specMis-measurement LOW: Minimal Current
PFR 130 BAU corrupting IDPU cmds IDPU DMA Channel Issue LOW: Hardware Modified
PFR 131 BAU corrupting IDPU cmds IDPU DMA Channel Issue LOW: Hardware Modified
PFR 147 BAU reset Break-out configuration MED: Operational complexity
PFR 161 Receiver lock prior to vib JPL Local transmitter LOW: No commands receivedPFR 172 K1 Battery Relay flipped GSE initial turn-on LOW: Only affected monitorSAI 0215 BAU reset and cmd loss GSE Power supply too low LOW: Non-Flight Configuration
SAI 0340 Thruster stops out of range. ITOS timing error LOW: Non-Flight Configuration
January 5, 2007 THEMIS Mission Readiness Review 67
Operational WorkArounds
PFR Probe System Problem Description Operational Work-around030 A-E IDPU PCB FPGA command lockout SAFE Before Actuation Retry075 A-E ESA ESA Surge Current Disable Current Trip in Turn On164 A-E ESA ESA Supply Noise when Off Turn On ESA 183 A EFI EFI V6 Selt-test Signal Loss Ignore EFI V6 Self Test205 A-E Thermal RCS Cold Spot w/ only secondary Turn On RCS Primary Heaters210 A-E BAU RCS Missing First Pulse Start Maneuvers w/ "Stop" cmd226 A Thermal Swapped Temperature Monitors Reverse mnemonics230 A-E BAU Inaccurate 20Hz thruster counter Use VC4 data for verification231 A-E BAU Inaccurate Command Timer Do not use command timer.0339 A-E BAU IRU Noisy Measurements Ignore first samples of ACS
PFR Probe System Problem Description Operational Work-around030 A-E IDPU PCB FPGA command lockout SAFE Before Actuation Retry075 A-E ESA ESA Surge Current Disable Current Trip in Turn On164 A-E ESA ESA Supply Noise when Off Turn On ESA 183 A EFI EFI V6 Selt-test Signal Loss Ignore EFI V6 Self Test205 A-E Thermal RCS Cold Spot w/ only secondary Turn On RCS Primary Heaters210 A-E BAU RCS Missing First Pulse Start Maneuvers w/ "Stop" cmd226 A Thermal Swapped Temperature Monitors Reverse mnemonics230 A-E BAU Inaccurate 20Hz thruster counter Use VC4 data for verification231 A-E BAU Inaccurate Command Timer Do not use command timer.0339 A-E BAU IRU Noisy Measurements Ignore first samples of ACS
January 5, 2007 THEMIS Mission Readiness Review 68
Integration and Test
Peter Harvey
Project Manager
January 5, 2007 THEMIS Mission Readiness Review 69
Integration Agenda
Recent Activities• Environmental Tests Completed
• Delivery to Astrotech
• Probe Processing
• Fueling Preparations
• Carrier Processing
Probe and Instrument Status• Instrument Status and Remaining Items
• Probe Status and Remaining Items
• Integration Plan
Review Process • RFAs in Work
• Reviews Ahead
January 5, 2007 THEMIS Mission Readiness Review 70
Environments
Thermal Vacuum
Acoustics
Spin Balance
EMC
VibrationMagnetics
January 5, 2007 THEMIS Mission Readiness Review 71
Probe Processing
Bolt Cutter Installation
Performance Tests
Solar Array Illumination
Delivery to ASO
January 5, 2007 THEMIS Mission Readiness Review 72
Probe Fueling Preps
FM2/FM3 Thermal Vacuum
Vibration
Thermal Vacuum
Acoustics Spin Balance
Storage
Dry Weigh & Pressurize Ready for Fuel
January 5, 2007 THEMIS Mission Readiness Review 73
Carrier Processing
Vibration Acoustics Spin Balance
Storage
PC Unload
SSS Installation
Ready for Probes
January 5, 2007 THEMIS Mission Readiness Review 74
Instrument Status
Instrument StatusFlight Hardware Ready
Flight Software Ready
Recent Activities
Performance Test
Remaining Items
ESC Verification
SST/ESA Covers
EFI Hats
Contamination Samples
Instruments F1 F2 F3 F4 F5IDPU Complete Complete Complete Complete CompleteFSW 4.02 4.02 4.02 4.02 4.02EFI Complete Complete Complete Complete CompleteESA Complete Complete Complete Complete CompleteSST Complete Complete Complete Complete CompleteFGM Complete Complete Complete Complete CompleteSCM Complete Complete Complete Complete CompleteMagBoom Complete Complete Complete Complete CompleteIntegration Complete Complete Complete Complete CompleteTest Complete Complete Complete Complete CompleteEMC CompleteTV Complete Complete Complete Complete CompleteMagnetics Complete Complete Complete Complete CompleteESA Recal Complete Complete Complete Complete Complete
Instruments F1 F2 F3 F4 F5IDPU Complete Complete Complete Complete CompleteFSW 4.02 4.02 4.02 4.02 4.02EFI Complete Complete Complete Complete CompleteESA Complete Complete Complete Complete CompleteSST Complete Complete Complete Complete CompleteFGM Complete Complete Complete Complete CompleteSCM Complete Complete Complete Complete CompleteMagBoom Complete Complete Complete Complete CompleteIntegration Complete Complete Complete Complete CompleteTest Complete Complete Complete Complete CompleteEMC CompleteTV Complete Complete Complete Complete CompleteMagnetics Complete Complete Complete Complete CompleteESA Recal Complete Complete Complete Complete CompleteIDPU FSW F1 F2 F3 F4 F5Image1 4.02 4.02 4.02 4.02 4.02Image2 4.02 4.02 4.02 4.02 4.02Image3 4.02 4.02 4.02 4.02 4.02Image4 4.02 4.02 4.02 4.02 4.02ETC 5.A 5.B 5.C 5.D 5.EF5.BEB B0-c B0-c B0-c B0-c B0-cF6.BEB B1-c B1-c B1-c B1-c B1-cF7.BEB B2-c B2-c B2-c B2-c B2-cF8.BEB B3-c B3-c B3-c B3-c B3-cF9.DFB D1 D1 D1 D1 D1FA.DAP 12 12 12 12 12
IDPU FSW F1 F2 F3 F4 F5Image1 4.02 4.02 4.02 4.02 4.02Image2 4.02 4.02 4.02 4.02 4.02Image3 4.02 4.02 4.02 4.02 4.02Image4 4.02 4.02 4.02 4.02 4.02ETC 5.A 5.B 5.C 5.D 5.EF5.BEB B0-c B0-c B0-c B0-c B0-cF6.BEB B1-c B1-c B1-c B1-c B1-cF7.BEB B2-c B2-c B2-c B2-c B2-cF8.BEB B3-c B3-c B3-c B3-c B3-cF9.DFB D1 D1 D1 D1 D1FA.DAP 12 12 12 12 12
January 5, 2007 THEMIS Mission Readiness Review 75
Probe Status
Probe StatusHardware Complete
Software Complete
Recent Activities at ASO
Performance Tests
Solar Array Illumination
RCS Pressurization to 1.1*MEOP
Dry Weigh
Remaining Items
Fueling
Flight Plugs
Integrate to PC
Attach Sep System
Probe F1 F2 F3 F4 F5Structures Complete Complete Complete Complete CompleteSep Systems Complete Complete Complete Complete CompleteSolar Arrays Complete Complete Complete Complete CompleteBAU 103 101 105 104 102FSW Image 1 V3.19 V3.19 V3.19 V3.19 V3.19FSW Image 2 V3.19 V3.19 V3.19 V3.19 V3.19RTS Complete Complete Complete Complete CompleteRCS Complete Complete Complete Complete CompleteTransponder Complete Complete Complete Complete CompleteAntenna Complete Complete Complete Complete CompleteBattery Complete Complete Complete Complete CompleteHarness Complete Complete Complete Complete CompleteIRU Complete Complete Complete Complete CompleteAEB Complete Complete Complete Complete CompleteBus CPT Complete Complete Complete Complete CompleteCTV Test CompleteInstrument I&T Complete Complete Complete Complete CompleteProbe CPT Complete Complete Complete Complete CompleteEMC CompleteVibration Complete Complete Complete Complete CompleteTV Complete Complete Complete Complete CompleteMagnetics Complete Complete Complete Complete CompleteSpin Balance Complete Complete Complete Complete CompletePressurize Complete Complete Complete Complete CompleteFuel Empty Empty Empty Empty EmptySafing Plugs NonFlight NonFlight NonFlight NonFlight NonFlight
January 5, 2007 THEMIS Mission Readiness Review 76
Integration Flow
Probe Fueling Probe RCS Electr. Verif.
Weigh Wet Probes, Attach Pyro
PCA Funct.Spin Balance
PCA Comm Check @ Blockhouse
Install Pyro Signal SMDC/ Weigh PCA
Engr Walk-down/ Trans- port Preps
Move Probes to HPF
Weigh PCA
PCA Mate to 3rd Stage/ Clamp-band Instl
Transport to Pad
S/C Functional & RF Test
Launch Rehearsal
Power On & Stray Voltage
Install Fairing
Prop. Load Prep
2nd Stage Fueling, Ordnance
Launch Readiness Review
La
un
ch
Sh
ipp
ing
fr
om
JP
L 12/08/06
12/21/06
02/02/07
02/15/0702/14/07
ASTROTECH and Launch Pad Flow
12/11/06 12/12/06
01/08/07
01/15/07
01/13/0701/05/0712/22/06
12/13/06
02/03/07 02/05/07 02/12/07 02/13/07
PCA Functional
01/23/0701/22/07
12/23/06 01/02/07
Reserve
Christmas Shutdown
12/11/06to
12/18/06
12/19/06
12/15/06
12/11/06
THEMIS Launch
01/03/07
02/07/0702/06/07
12/15/0612/14/06 12/19/0612/15/06 12/20/0612/19/06
5 Probes plus EGSE, MGSE at ASO
Probe Carrier Unpack
Unpack, Setup EGSE
PC-VCO Electrical Test
Install Sep. Harness
Install SMDC Lines
F1 RCS MEOP, LPT, S/A Test
Install Bolt Cutters, Therm. Closeouts
F2-3 RCS MEOP, LPT, S/A Test
F4-5 RCS MEOP, LPT, S/A Test
Weigh, Move to Stands
Pre-VosMRR (GSFC)
01/0301/05
LVRR (KSC) 01/12
Media Day 01/12
01/09/07 01/10/07 01/11/07 01/12/07
MRR (HQ) 01/23
01/24/07 01/25/07 01/26/07 01/27/07 01/29/07 01/30/07
LSRR (CCAFS) 02/01
01/3107 02/01/07
02/09/0702/08/07
LMCM (KSC) 02/13FRR (KSC) 02/12
January 5, 2007 THEMIS Mission Readiness Review 76
January 5, 2007 THEMIS Mission Readiness Review 77
RFAs
Issue SubmittedRCS Proof Tests Jan 17 2006BAU EEPROM Signal Plots Jun 23 2006Energy Balance in Deep Eclipse Jun 26 2006Launch Window Analysis Nov 09 2006
Issue SubmittedRCS Proof Tests Jan 17 2006BAU EEPROM Signal Plots Jun 23 2006Energy Balance in Deep Eclipse Jun 26 2006Launch Window Analysis Nov 09 2006
RFA StatusIncomplete: 0
Complete: 308
Closed: 304
Total: 308
Final Four Closure Method• RCS Proof Issue: Expected to Close with Risk Definition• BAU EEPROM Plots Provided were Insufficient to the reviewer
but it is no longer practical to obtain better plots.• Energy Balance was Provided using Best Thermal Model at the
time. Reviewer repeated request using new mission profile and correlated thermal model. This was delivered in December.
• Launch Window Analysis will be reviewed by GSFC by 1/15/07
January 5, 2007 THEMIS Mission Readiness Review 78
Reviews Ahead
Start Event Description1/5/2007 MRR Mission Readiness Review
1/12/2007 LVRR Launch Vehicle Readiness Review1/19/2007 SMSR Systems and Safety Mission Assurance1/23/2007 MRB Mission Readiness Review2/1/2007 LSRR Launch Site Readiness Review
2/12/2007 FRR Flight Readiness Review 2/13/2007 LRR Launch Readiness Review
January 5, 2007 THEMIS Mission Readiness Review 79
Operations
Peter Harvey
Project Manager
January 5, 2007 THEMIS Mission Readiness Review 80
Operations Agenda
Ground Systems Development• Ground System Diagram• Mission Operations Center• Ground Stations• RF Licencing• Security• Software• Procedures• Verification and Training• GSFC Support
Launch and Early OrbitContacts Ground Based Observations
January 5, 2007 THEMIS Mission Readiness Review 81
Ground System Diagram
Ground System Elements•Ground Stations
•Ground Network
•Space Network
•Mission Operations Center
•Science Operations Center
•Flight Dynamics Center
Including•Mission Design
•Orbit & Attitude Determination
•Maneuver Planning
•Limit Detection and Notification
•Network Security
January 5, 2007 THEMIS Mission Readiness Review 82
Mission Operations Center
BGS Antenna, Equipment Racks and FOT Workstations at the Mission Operations Center
January 5, 2007 THEMIS Mission Readiness Review 83
MOC Expansion
January 5, 2007 THEMIS Mission Readiness Review 84
Ground Stations
Ground StationStation
DesignatorFigure of
MeritLocation Function
Berkeley, CA BGS 11-m 24.0 dB/K37.879° N 122.243° W
Primary TLM/CMD/TRK
Wallops Island, VA WGS 11-m 23.0 dB/K37.925° N75.476° W
Secondary TLM/CMD/TRK
Merritt Island, FL MILA 9-m 1/2 21.6 dB/K28.508° N80.693° W
Secondary TLM/CMD/TRK
Santiago, Chile AGO 9-m 21.6 dB/K33.151° S70.668° W
Secondary TLM/CMD/TRK
Hartebeesthoek, SA HBK 10-m 20.4 dB/K25.883° S27.708° E
Secondary TLM/CMD/TRK
Mission Supported by 5 Ground Stations• Ground Stations: BGS, WGS, MILA, AGO, HBK• GN, SN and FDF Support Documented in PSLA• All Stations Have Successfully Flowed Data with MOC
January 5, 2007 THEMIS Mission Readiness Review 85
NTIA License
NTIA License Status• Identical Frequency Pairs for All Probes Assigned by GSFC
Spectrum Management Office– Telemetry: 2282.5 MHz– Command: 221 / 240 × 2282.5 = 2101.802083 MHz– DoD Approved Frequency Assignment
• Stage 4 License Approved– Stage 2 Application Was Submitted to NTIA in June 2004– Reviewed by Space Frequency Coordination Group (SFCG) at
Meeting in November 2004– Stage 2 License Was Approved in December 2004– Stage 4 License Was Approved in February 2006
January 5, 2007 THEMIS Mission Readiness Review 86
IT Security
Security Measures• Physical Security
– Facilities Locked and Protected by Alarm System– Access Controlled by University of California Police Department
• Network Security– Tight Access Rules on Firewalls– Regular Password Changes
• Document Access– Critical Documents and Databases Kept Confidential
• Personnel– Screening and Background Checks Complete– Establishment and Enforcement of Rules of Behavior
January 5, 2007 THEMIS Mission Readiness Review 87
Software Status
Tool Developer Function Platform Comments / Status
MDT UCB IDL Based THEMIS Mission Design Tool, Calls GTDS and GMAN for Orbit Propagation and Finite Maneuver Targeting
Solaris Operational in MOC
GTDS GSFC Orbit Propagation, Orbit Determination, Ephemeris Generation
Solaris Version 2003.01 Operational in FDC
GMAN GSFC Finite Maneuver Targeting and Reconstruction
Solaris Version 1994.03PC Operational in FDC
SatTrack BTS Pass Scheduling, Product Generation, Networking, 3-D Visualization, Ground Station Control
Solaris, Linux
Version 4.6.1 Operational in MOC, FDC and BGS
MSASS GSFC Attitude Determination Solaris, Windows XP
Version 2005.03 To Be Installed in MOC and FDC by L - 2 Months
CALIBATT GSFC Attitude Maneuver Calibration
Solaris, Windows XP
Version 2005.01 Operational in FDC
January 5, 2007 THEMIS Mission Readiness Review 88
Software Status
Tool Developer Function Platform Comments / Status
ITOS Hammers Probe Command and Control, Telemetry Monitoring, Limit Checking
Solaris, Linux
Version 703p1-6 Operational in MOC, FlatSat and EGSE
VirtualSat Hammers Dynamics Probe Simulation
Windows XP Supplied with FlatSat West – Operational in FlatSat
BMPS UCB ATS Load Generation Solaris Operational in MOC
SERS MF Spacecraft Emergency Response System
Windows NT Operational at MOC
BTAPS UCB Probe Bus and Instrument Trend Analysis
Solaris Operational in MOC
MOC Software CompleteCurrently Under Pre-Launch Software Freeze
January 5, 2007 THEMIS Mission Readiness Review 89
Procedures
ID LEO PROCEDUREthm-fop-proc-001 THEMIS Probe Separation thm-fop-proc-002 THEMIS Probe Checkout Procedure (round-robin)thm-fop-proc-003 THEMIS Probe Latch Valves Open and Maneuver Checkoutthm-fop-proc-004 THEMIS Probe Sun-Normal Attitude Manueverthm-fop-proc-005 THEMIS Probe Maneuver Pass Procedurethm-fop-proc-006 THEMIS Pyro Valve Open Procedurethm-fop-proc-101 THEMIS IDPU Power-On and Check-out Procedurethm-fop-proc-102 THEMIS FGM Commissioning Procedurethm-fop-proc-103 THEMIS SCM/EFI Commissioning Procedurethm-fop-proc-104 THEMIS Mag Boom Deploy Procedurethm-fop-proc-105 THEMIS SST Commissioning Procedurethm-fop-proc-106 THEMIS ESA Commissioning Procedurethm-fop-proc-107 THEMIS ESA HV Ramp Up Procedurethm-fop-proc-108 THEMIS ESA Cover Open Procedurethm-fop-proc-109 THEMIS SPB Door Open Procedurethm-fop-proc-110 THEMIS SPB Motor Deploy Procedurethm-fop-proc-111 THEMIS AXB Deploy Procedurethm-fop-proc-112 THEMIS SDT Upload Procedurethm-fop-proc-113 THEMIS IDPU EEPROM/RAM Load Order Form
ID LEO PROCEDUREthm-fop-proc-001 THEMIS Probe Separation thm-fop-proc-002 THEMIS Probe Checkout Procedure (round-robin)thm-fop-proc-003 THEMIS Probe Latch Valves Open and Maneuver Checkoutthm-fop-proc-004 THEMIS Probe Sun-Normal Attitude Manueverthm-fop-proc-005 THEMIS Probe Maneuver Pass Procedurethm-fop-proc-006 THEMIS Pyro Valve Open Procedurethm-fop-proc-101 THEMIS IDPU Power-On and Check-out Procedurethm-fop-proc-102 THEMIS FGM Commissioning Procedurethm-fop-proc-103 THEMIS SCM/EFI Commissioning Procedurethm-fop-proc-104 THEMIS Mag Boom Deploy Procedurethm-fop-proc-105 THEMIS SST Commissioning Procedurethm-fop-proc-106 THEMIS ESA Commissioning Procedurethm-fop-proc-107 THEMIS ESA HV Ramp Up Procedurethm-fop-proc-108 THEMIS ESA Cover Open Procedurethm-fop-proc-109 THEMIS SPB Door Open Procedurethm-fop-proc-110 THEMIS SPB Motor Deploy Procedurethm-fop-proc-111 THEMIS AXB Deploy Procedurethm-fop-proc-112 THEMIS SDT Upload Procedurethm-fop-proc-113 THEMIS IDPU EEPROM/RAM Load Order Form
ID LEO CONTINGENCY PROCEDUREthm-cop-proc-001 THEMIS Cold Reset Recovery Procedurethm-cop-proc-002 THEMIS Load Shed Recovery Procedurethm-cop-proc-003 THEMIS Mag Boom Back-up Deploy Procedurethm-cop-proc-004 THEMIS AXB Back-up Deploy Procedurethm-cop-proc-005 THEMIS ESA Back-up Cover Open Procedurethm-cop-proc-006 THEMIS Latch Valve Anomaly Procedurethm-cop-proc-007 THEMIS Inadvertent Firing of Pyro Valve Contingency Procedurethm-cop-proc-008 THEMIS BAU FSW Image Uploadthm-cop-proc-009 THEMIS IDPU FSW Image Upload
ID LEO CONTINGENCY PROCEDUREthm-cop-proc-001 THEMIS Cold Reset Recovery Procedurethm-cop-proc-002 THEMIS Load Shed Recovery Procedurethm-cop-proc-003 THEMIS Mag Boom Back-up Deploy Procedurethm-cop-proc-004 THEMIS AXB Back-up Deploy Procedurethm-cop-proc-005 THEMIS ESA Back-up Cover Open Procedurethm-cop-proc-006 THEMIS Latch Valve Anomaly Procedurethm-cop-proc-007 THEMIS Inadvertent Firing of Pyro Valve Contingency Procedurethm-cop-proc-008 THEMIS BAU FSW Image Uploadthm-cop-proc-009 THEMIS IDPU FSW Image Upload
Procedure & Display Status• All 19 Flight Ops Procedures Ready• All 9 Contingency Ops Procedures Ready• All 178 Computer Procs Ready• All Computer Displays Ready
January 5, 2007 THEMIS Mission Readiness Review 90
Verification & Training
Verification and Training Program• Operations Identified 238 Verification and Training Exercises• Currently 90% Are Complete. Expecting 97% by Jan 15th
• All Launch Critical Exercises Completed This Week– Fuel Record Keeping– Closed Loop Maneuver Sims
• Launch Simulation in PCA Configuration Successful at JPL• Launch Simulation is Planned Two More Times (ASO & PAD)• Continuing Pass Simulations with Combined UCB/Swales Team• Mission Dress Rehearsal at L-2 with MOC and GSFC/FDF
January 5, 2007 THEMIS Mission Readiness Review 91
GSFC Support• FDAB Support
– MSASS Upgrade Including Kalman Filter and Usage Support– GTDS Software Upgrade and Usage Support– GMAN Support and Validation of Maneuver Scenarios– CALIBATT Support for Attitude Maneuver Calibration
• FDF Support– Assignment of BGS Transmit and Receiver Tracker IDs– Verification of BGS Two-way Doppler Tracking– Pre-launch Data Flows – Orbit Determination Pre-Launch SImulations– Orbit Determination Post-Launch Support
• SCP Support– Network Operations Support– Ground Network Support– Space Network Support (TDRSS)
GSFC Support
January 5, 2007 THEMIS Mission Readiness Review 92
LEO Operations
LEO Operations• State Vector Delivered to UCB via email @ SECO-2 (65min)• Monitoring of Probe Separation via TDRSS
– Top Probe Will Be Commanded to Transmit at T+70 mins– Separation will occur at T+73 minutes – All Probes Will Be Recording Engineering Data– Separation Recorded by Each Probe Individually– Engineering Data Dumped in Later Passes
• Probes Are Released at Good Sun Angle, Power Positive– 43 degrees Side to Sun
Probe A Released First
Probes B−E Released Simultaneously 3 s Later
All Probes Independent of Each Other
January 5, 2007 THEMIS Mission Readiness Review 93
LEO Acquistion
LEO AcquisitionMultiple Ground Assets Have Good View Following LaunchProbe Attitude Around 1:30 MET is Poor for Telemetry Probes Contacted at 4Kbps for 5 Minutes each from 1:20 to 1:40
January 5, 2007 THEMIS Mission Readiness Review 94
LEO Early Orbit
Early Orbit Activities• First Real Round-robin Contacts
– Starting about T+2hr, Each Probe Will Be Contacted for 10 Mins– Rest Period between Probe Contacts of 5 Mins– Expected Battery SOC to Remain > 87%
• Initial Orbit and Attitude Determination– Record and Process Two-way Doppler Data– Perform Attitude Determination in Real-time– Both UCB and GSFC FDF Function in Parallel
• Round-Robin Checkout of Key Systems on Each Probe– Reaction Control System Readiness– Attitude Sensors Functionality
• Perform Attitude Maneuver to Ecliptic Normal– If Power Negative, Will Maneuver on First Orbit. – Improves Power and Communications Coverage
• Systematic Instrument Power-up and Check-out– Leads to Decision of Probe Orbit Placement in Appx 26 Days
January 5, 2007 THEMIS Mission Readiness Review 95
LEO Orbit Placement
Orbit Placement Decision• Decision Based on Probe Bus and Instrument Checkout
– Probe Bus RCS, ACS and Power System– Unable to Check Probe Thermal System Entirely– Instrument Check-out of FGM, SCM, SST and ESA– Unable to Check EFI with AXB & SPB Booms Stowed
• PI Team Members Involved in Probe Placement Decision– PI, PM, MSE, MOM, Swales Probe Bus Systems Lead,
Instrument Scientists, GSFC Program Manager and GSFC Project Scientist
• Assignment of Constellation IDs– According to Probe Placement Decision
January 5, 2007 THEMIS Mission Readiness Review 96
LEO Probe Identification
Probe Bus / Simulator Name
Probe Bus ID
Instrument Suite ID
CCSDS V1 Command
SCID
CCSDS V1 Telemetry
SCID
NASA Support Identification
Code
Satellite Catalog
Number *
International Designator *
Constellation Identifier **
THEMISFlatSat West N/A N/A 0x150 0x150 N/A N/A N/A N/A
THEMIS A F1 FM1 0x153 0x153 0451 99001 2007-001A P1
THEMIS B F2 FM2 0x151 0x151 0452 99002 2007-001B P2
THEMIS C F3 FM3 0x155 0x155 0453 99003 2007-001C P3
THEMIS D F4 FM4 0x154 0x154 0454 99004 2007-001D P4
THEMIS E F5 FM5 0x152 0x152 0455 99005 2007-001E P5
THEMIS Spare N/A N/A 0x156 0x156 N/A N/A N/A N/A
THEMISFlatSat East N/A N/A 0x157 0x157 N/A N/A N/A N/A
* Assigned after Launch ** Assigned after Probe Placement Decision
LEO Probe Identification• Provides Unique Relationship between Various Probe Identifiers• Extensively Tested during Mission Integration
January 5, 2007 THEMIS Mission Readiness Review 97
Contacts - Typical
Entire Ground Station View Periods at Nominal Low Data Rate of 4.096 kbps
January 5, 2007 THEMIS Mission Readiness Review 98
Contacts - Total
Ground Station Contact Summary• Number of Passes Based on Detailed 2-Year Mission Design
– BGS 11-m (Primary)– WGS 11-m, MILA 9-m, AGO 9-m and HBK 10-m (Secondary)
• Passes Included to Support Routine and Special Operations– Daily BGS Contacts with All Probes for State-of-health Monitoring– Maneuver Support, Instrument Commissioning, Doppler Tracking
ProbeBGS WGS AGO HBK
L&EO Science L&EO Science L&EO Science L&EO Science
1 150 750 60 50 30 20 20 20
2 150 750 60 90 30 20 20 30
3 150 750 60 20 30 20 20 20
4 150 750 60 20 30 20 20 20
5 150 750 60 150 30 60 20 40
Subtotal 750 3750 300 330 150 140 100 130
Total Contacts
4500 630 290 230
January 5, 2007 THEMIS Mission Readiness Review 99
Contacts - TDRSS
TDRSS Contact Summary• Launch Support
– Monitoring of Probe A Separation
• Maneuver Support Near Perigee for All Probes– Apogee Change for Mission Orbit Placement – Initiation of Reentry
• Contingency Support for All Probes– Only Few TDRSS Contingency Support Hours Required
ProbeTDRSS Support
Launch Maneuver Contingency
1 1 h 19 h 2
2 19 h 2
3 2 h 2
4 2 h 2
5 5 h 2
Subtotal 1 h 47 h 10 h
Total Support 58 h
January 5, 2007 THEMIS Mission Readiness Review 100
Ground Based Observatories
Ground Based Observatories • UCB has Delivered All 20 GBO (GMAG and ASI) units• 19 Have Been Installed, 1 Needs Repair• Automatic Data Collection and Archiving in Progress• Remote Commanding and Diagnostics Working • Expect to be Fully Functional at Winter 2008
Courtesy H.Frey, UCB
GeographicLongitude 324°
Geographic Longitude 195°
GeomagneticNorth Pole
GeographicNorth Pole
January 5, 2007 THEMIS Mission Readiness Review 101
Ground Observatory Status
Unit # Location StatusGB0#02 Athabasca Operating normallyGB0#03 Prince George Down for Repair (/1)GB0#04 Ekati Diamond Mine Operating normallyGB0#06 The Pas Operating normallyGB0#07 Whitehorse Operating normallyGB0#08 Inuvik RF Interference (/2)GB0#09 Rankin Inlet RF Interference (/2)GB0#10 Fort Smith Operating normallyGB0#11 McGrath Operating normallyGB0#12 Fort Yukon Operating normallyGB0#13 Univ. of Calgary To Be Installed at NainGB0#14 Goose Bay RF Interference (/2)GB0#15 Kapuskasing Operating normallyGB0#16 Pinawa Operating normallyGB0#17 Chibougamau Operating normallyGB0#18 Gakona Operating normallyGB0#19 Gillam Operating normallyGB0#20 Kiana Operating normallyGB0#21 Ft. Simpson Operating normallyGB0#22 Sanikiluaq Operating normally
Ground Based ObservatoriesUnit # Location StatusGB0#02 Athabasca Operating normallyGB0#03 Prince George Down for Repair (/1)GB0#04 Ekati Diamond Mine Operating normallyGB0#06 The Pas Operating normallyGB0#07 Whitehorse Operating normallyGB0#08 Inuvik RF Interference (/2)GB0#09 Rankin Inlet RF Interference (/2)GB0#10 Fort Smith Operating normallyGB0#11 McGrath Operating normallyGB0#12 Fort Yukon Operating normallyGB0#13 Univ. of Calgary To Be Installed at NainGB0#14 Goose Bay RF Interference (/2)GB0#15 Kapuskasing Operating normallyGB0#16 Pinawa Operating normallyGB0#17 Chibougamau Operating normallyGB0#18 Gakona Operating normallyGB0#19 Gillam Operating normallyGB0#20 Kiana Operating normallyGB0#21 Ft. Simpson Operating normallyGB0#22 Sanikiluaq Operating normally
Ground Based Observatories
/1: Supply Down/2: Radar RF Noise
January 5, 2007 THEMIS Mission Readiness Review 102
Launch Day
Frank Snow
Mission Manager
January 5, 2007 THEMIS Mission Readiness Review 103
THEMIS Launch Day Management Flow
GSFC Network Operations Manager
Arnie Rausch
NASA Eng Team
NASA ChiefEngineer
James Wood
NASA Advisory Team
NASA AdvisoryManager
Joe Lackovich
NASA Launch ManagerChuck Dovale
Boeing Mission Director
Rich Murphy
NASA ENGINEERING Go / No-Go
ADVISORY
NASA Go / No-Go
MDC LVDC
MDC
MDC
Safety & Mission AssuranceRick Boutin
MDC
NASA SMAGo / No-Go
NASA ALM
NASA MIT
MissionIntegration Manager
Garrett Skrobot
MISSION INTEGRATIONGo / No-Go
Spacecraft Mission Director
Frank Snow
Go / No-Go
INFO
MDCMDC
SMDGo / No-Go
THEMIS Project Manager
Peter Harvey
Ground Operations Manager
Donald GatesMDC
Go / No-Go
MDC
NASA SMA Team
GSFC Safety & Mission Assurance
ManagerRon Perison MDC
Go / No-Go
Spacecraft Test ConductorDave Curtis
LVDC
Go / No-GoGSFC
Go / No-Go
Spacecraft I&T Manager
Rick SterlingASO
MissionOperations Manager
Manfred BesterMOC
Go / No-GoGo / No-Go
Go / No-Go
January 5, 2007 THEMIS Mission Readiness Review 104
THEMIS Launch Decision Flow
LVDC-3
Astrotech(ASO)
UCB Mission Operations Center
(MOC)
Go/No-Go
LaunchDecision
MissileChief Engineer
(Boeing)
Vehicle Status
OperationsBuilding (OB)
Status
Mission Director Center (MDC)
MissionDirector(Boeing)
Status
RangeCoordinator
(Boeing)
StatusLaunchConductor(Boeing)
LaunchDirector(Boeing)
LaunchConcur
Range Operations
Control Center
• Range Safety Status
• Range Status
• Weather• Support Range Status (LV)
RangeControl Officer
LVDC
Launch VehicleSystems
Engineering(Boeing)
WINDS(Boeing)
NASA AdvisoryManager
(KSC)
Dir. of Eng.(Boeing)
Status
L/V Sys Status
Advisory
CMDRS NET
USAF45 SW/CCSpace Lift
Commander(SLCC)
NASAChief Engineer
(KSC)
Status
Go/No-Go
Go/No-Go
NASAMission
IntegrationMngr (KSC)
NASALaunchManager
(KSC)
Go/No-Go
StatusNASASpacecraft
Coordinator(KSC)
Go/No-Go
AF SiteDirector(1 SLS)
AF LaunchCrew
Commander(1 SLS)
Status
OperationsIntegrator(Boeing) Go/No-Go
MDC OpsDirector
(KSC)
SpacecraftTest
Conductor(UCB)
Go/No-Go
Go/No-Go
Status
Go/No-Go
Status
Spacecraft Mission Director(GSFC)
THEMISProject Manager
(UCB)
GSFCSafety & Mission Assurance Mngr
(GSFC)
NASASafety & Mission Assurance Mngr
(KSC)
Go/No-Go
Go/No-Go
SpacecraftI&T Manager
(UCB)
Go/No-Go
GroundOperations
Manager(GSFC)
GSFC Network Operations
Manager (GSFC)
GSFC
Go/No-Go
Go/No-Go
NASAEngineeringTeam (KSC)
Go/No-GoMission
Operations Manager
(UCB)
Go/No-Go
January 5, 2007 THEMIS Mission Readiness Review 105
THEMIS Anomaly Resolution
Spacecraft Only
Anomaly
NASA Launch Manager's Net
LaunchVehicle / Integrated Anomaly
Boeing SLC-17 TeamNASA Engineering Team
Boeing HB Engineering Team
NLMNASA Launch Manager
Chuck Dovale
MDMission Director
Rich Murphy
MCEMissile Chief Engineer
Steve Huff
VSEVehicle Systems Engineer
Greg Radle
NASA CENASA Chief Engineer
James Wood
MissionManagement
Net
Anomaly Team
Anomaly NetOr
Boeing Mgmt Net
Anomaly NetOr
Boeing Mgmt Net
CLCDRLaunch Conductor
Bob Godin
DEDirector of Engineering
Dave Crosse
Integrated Anomaly Only
S/C Eng / Ops Team
Resource Protection
USAF CX-17 Engineering Team
LDLaunch DirectorMark Dowhan
MSEMission Systems Engineer
Stu Harris
ARCUSAF Anomaly Resolution Chief
Bryan Buckley
SMDSpacecraft Mission
DirectorFrank Snow
VIP SEATING AREA
-Network Drop for LaptopsXXXX
THEMIS Mission Director’s Center
BOEINGKRIS WALSHASST MISSION DIRECTOR
BOEINGRICH MURPHYMISSION DIRECTOR
ANALEX/KSCTRACY EVANSASST MISSION OPS DIR
NASA/KSCTUAN DOANMISSION OPS DIRECTOR
1ST SLSMAJ PAUL CAZIERDEPUTY AF SITE DIR
AEROSPACERANDY MOYERAIR FORCE ADVISOR
1ST SLSLT COL MYRON FORTSONAIR FORCE SITE DIR
NASA/KSC RICK BOUTINSAFETY & MSN ASSUR
NASA/KSCBERT GARRIDOSMA MISSION MGNT REP
NASA/HQWILLIS JENKINSPROGRAM EXECUTIVE
NASA/HQMIKE LUTHERSCIENCE MISSION DIR
BOEINGMARK WILKINSVICE PRES DELTA PROG
BOEINGDAVE CROSSEDIRECTOR OF ENGR
BOEING MIKE KENNARDOPERATIONS INTEGRATOR
BOEINGMIKE TAYLORFLIGHT OPS MANGER
NASA/HQBILL WROBELSPACE OPS MSN DIR
NASA/KSCJOE LACKOVICHNASA ADV MNGR
NASA/KSCSTEVE FRANCOISNASA ADVISOR
NASA/KSCOSCAR TOLEDONASA ADVISOR
26
25
28
27
6-4525
6-4526
6-4527
6-4528
MOD
AM
OD
6-4529
6-4530
30
29
SMA
MM
R
32
31
HQM
GCD
NAM
6-4531
6-4532
6-2242
KSA
KPM
6-4535
6-4536
6-4533
6-4534
36
34
33
35
KCD
NASA/KSC BILL PARSONSNASA ADVISOR
BOEINGSCOTT MESSERNLS PROGRAM MANAGER
21
43
65
AMD
MD
6-4501
6-4502
6-4503
6-4504
6-4505
6-4506
AFA
DA
FS
DA
FS
D
87
12
10
91
1
6-4507
6-4508
6-4509
6-4510
6-4511
6-4512
OI
DED
VPF
O
14
13
16
15
18
17
6-4513
6-4514
6-4515
6-4516
6-4517
6-4518
20
19
24
22
21
23
6-4519
6-4520
6-4521
6-4522
6-4523
6-4524
SMD
GS
MA
6-2241
6-2241
NASA/GSFCED WEILERGSFC CENTER DIRECTOR
NASA/GSFCFRANK SNOWS/C MISSION DIR
NASA/GSFCDONNIE GATESGROUND OPS MNGR
NASA/GSFCRON PERISONGSFC SAFETY & MISSION ASSURANCE
NASA/GSFCRICK OBENSCHEINFLT PROGRAMS DIR
UCBPETER HARVEYTHEMIS PROJ MNGR
UCBVASSILIS ANGELOPOULOSPRINCIPAL INVESTIGATOR
GO
MT
PMP
IF
PD
O N
ET
O N
ET
O N
ET
O N
ET
B N
ET
B N
ET
B N
ET
B N
ET
B N
ET
B N
ET
B N
ET
B N
ET
B N
ET
ANALEX TRACEY POSTLAUNCH OPS MNGR
NASA/KSCTBDNLM AWARD SEAT
FPO
NA
SA
M
IMA
LMN
LM
NASA/KSCAMANDA MITSKEVICHFLT PROJECTS OFFICE
NASA/KSCGARRETT SKROBOTNASA MSN INTEG MNGR
NASA/KSCCHUCK DOVALENASA LAUNCH MNGR
NASA/KSC OMAR BAEZASST LAUNCH MNGR
LOM
HQ
PX
HQ
SM
D
DPM
BOEINGTBD
BOEINGTBD
January 5, 2007 THEMIS Mission Readiness Review 106
January 5, 2007 THEMIS Mission Readiness Review 107
17
18
19
20
21
22
23
24
91
01
11
21
31
41
51
6 82
14
36
57
K-N
ET
THEMIS Mission Support LVDC-3
K-N
ET
Ron JacksonUCB
Linda WarnockJBOSC
Norm WhiteANALEX MGMT
Jan McMillenANALEX
Charlie FloydANALEX MGMT
Roy FisherANALEX
Tiffany NailNASA/KSC
Larry Ellis ANALEX MGMT
ReservedNASA KSC
6-45736-4574
6-45756-4576
6-45816-4582
6-45836-4584
6-45806-4579
6-45786-4577
K-N
ET
Steve Owens SAIC MGMT
-Network Drop for LaptopsXXXX
Joe BolekGSFC
Mike CulleySWALES
Paul TurinUCB
John ThurburGSFC
Jamey BurgetGSFC
Warren ChenSWALES
Dennis LeeGSFC
Jeremy McCauleyUCB
Greg DaltonUCB
Dave CurtisUCB STC
Stu HarrisUCB MSE
ReservedNASA KSC
ReservedNASA KSC
ReservedNASA KSC
O N
ET
O N
ET
O N
ET
O N
ET
O N
ET
O N
ET
O N
ET
O N
ET
O N
ET
O N
ET
O N
ET
O N
ET
January 5, 2007 THEMIS Mission Readiness Review 108
• THEMIS Spacecraft Recycle Requirements– Same day recycle
» Spacecraft will remain on internal power
– 24 hour recycle» Return to external power» Recharge Batteries – Remotely (Does Not Require Fairing Access)
– 48 hour recycle» Same as 24 hour recycle
– Multiple scrub limits» Same as 24 hour recycle» If extended delay» Continue to Recharge Batteries – Remotely (Does Not Require Fairing
Access)
THEMIS Mission Recycle Requirements
January 5, 2007 THEMIS Mission Readiness Review 109
THEMIS Mandatory Launch Constraints
January 5, 2007 THEMIS Mission Readiness Review 110
THEMIS Required Launch Constraints
January 5, 2007 THEMIS Mission Readiness Review 111
Launch Vehicle Readiness
Garrett Skrobot
Mission Integration Manager
January 5, 2007 THEMIS Mission Readiness Review 112
Mission Overview
January 5, 2007 THEMIS Mission Readiness Review 113
Launch Vehicle Overview• Vehicle Configuration: Delta 7925–10C• Launch Site: Eastern Range (ER), SLC-17B at
Cape Canaveral Air Force Station (CCAFS)• Mission Specifics:
– Perigee: 435 km, Apogee: 91845 km– Orbit Inclination: 16 degrees– Spacecraft (SC) Mass (will not exceed)
» 829 kg (2832.94lb) 775.60 kg actual– STAR 48B Motor
» Nutation Control System» Yo-Yo de-spin system
• Spin rates: – During Third Stage operation - max 70 rpm– S/C after spin-down and separation - 162 rpm
• Mission Unique– 3712 Bolted PAF– Sep System (at PAF/PC Interface)
• Non-Standard Services– Category 1 Analysis
» (1st 7925-10C ER)– Five - 24” Doors– Two 61 pin connectors– Fairing Cleaning to VC 6
• Separation System provided by THEMIS Spacecraft, contracted through Launch Services Program (LSP)NASA Launch Service (NLS) Contract
January 5, 2007 THEMIS Mission Readiness Review 114
Mission Parameters
• Launch Period 15 February 07 – 14 March
07
• Daily Launch Opportunities
–Single flight azimuth/SECO 1 trajectory 93 Deg
–Single Second Stage restart/Third Stage trajectories
–Window Duration 19.6 min• Launch period has been divided into two blocks of dates Opening
15 February to 28 February 23:08:00 UTC (Changes by 3:34
per day)
01 March to 14 March 21:57:00 UTC (Changes by 3:34 per day)
–Liftoff times are rounded to the nearest whole minute
–Mission Assurance Collision Avoidance (COLA) Measures will be accomplished
• Free Molecular Heating Rate at Fairing Separation < 0.1 BTU/ft2/sec
• Sun Angle Constraints: Centerline during coast 90 +/- 9 deg
January 5, 2007 THEMIS Mission Readiness Review 115
THEMIS PCS and Performance Margin
15-28 Feb 2007 01-14 Mar 2007
• Spacecraft Mass Including Probe Carrier (lb) 1709.91 1709.91
• Second Stage Velocity Reserve at SECO 2 (fps) 1735 1970
• Second Stage Velocity Reserve Required 268 268
for PCS of 99.7% (fps)
• TAG Performance Allowance (fps) 75 75
• Velocity Reserve Margin (fps) 1392 1627
January 5, 2007 THEMIS Mission Readiness Review 116
Depletion Burn:Removes Stage 2 fromvicinity of spacecraft,while lowering Stage 2 perigee altitude andorbit inclination
Flight Profile
Liftoff
MECOt = 263.3 secAlt = 69.0 nmiVI = 20,060 fps
Second Stage Ignitiont = 276.8 secAlt = 72.9 nmiVI = 20,068 fps
Fairing Jettisont = 281.0 secAlt = 74.1 nmiVI = 20,103 fps
SECO 1t = 593.5 secAlt = 101.9 nmiVI = 25,923 fps
ORBIT:100 x 304 nmi28.50 deg inclination
Second Stage Restartt = 3859.4 secAlt = 282.7 nmiVI = 24,662 fps
SECO 2t = 3915.1 secAlt = 280.6 nmiVI = 25,778 fps
ORBIT:280 x 825 nmi26.58 deg inclination
TECOt = 4091.6 secAlt = 305.2 nmiVI = 33,975 fps
Separate Probe At = 4380.1 secAlt = 658.6 nmiVI = 32,368 fps
Orbit:235 x 49,592 nmi16.00 deg inclination-40.00 deg arg of per
SRM Impact SRM Impact
SRM Jettison (6)t = 66.0 / 67.0 secAlt = 9.9 / 10.2 nmiVI = 3,231 / 3,269 fps
SRM Jettison (3)t = 131.5 secAlt = 31.3 nmiVI = 8,018 fps
Third Stage Ignitiont = 4005.1 secAlt = 281.0 nmiVI = 25,775 fps
Note: Values shown are for 15-28 Feb 2007 launch
January 5, 2007 THEMIS Mission Readiness Review 117
Orbit Trace – 15-28 Feb 2007
TEL4 = Eastern RangeANT = AntiguaCAIR = Cairns (Mobile Telemetry, MT)KWAJ = KwajaleinUCB = Berkeley Ground Station
Working with Big Crow to see if they can
overlap SC separation coverage
January 5, 2007 THEMIS Mission Readiness Review 118
Telemetry Asset Plan/Acquisition
Asset Acquisition StatusTEL-4 - Eastern Range Station at KSC Complete
ANT - Eastern Range Station at Antigua Complete
Cair - Cairns (Big Crow) Complete
KWAJ - Kwajalein Complete
January 5, 2007 THEMIS Mission Readiness Review 119
Accepted/Open Risks
ItemApproach
Risk ID
Status
Risk Description
1 A V0015
9 Flight critical engine section components are unqualified for the newly revised P95/50 MEFL MECO transient environment.
Risk accepted by LSP 4/24/02, (Ref ERB 01377KSC0 and ERB 02-23)
2 A V0037
Condition: Power and Control (P&C) Box capacitors have become loose in S/N 20070. Consequence: Undetected loose capacitors in other P&C Boxes.
Risk accepted by LSP 8/16/05, (Ref ERB-03-426; ERB 04-176)
3 A V0035
A photodiode failed within Redundant Inertial Flight Control Assembly (RIFCA) S/N 20093.
Risk accepted (Ref ERB 04-479). 6/8/06 ERB accepted S/N 20083 and all RIFCA after.
4 A V0033
Condition: Cracks have occurred and been detected within Electronics Package (E-Package) Thick Film Assemblies (TFA's).
Risk accepted by LSP 8/18/05 (Ref ERB 04-378; ERS-02-43; ERS-05-214 ERS-06-147).
S = Safety & Mission Assurance Designator
P = LSP Designator
5
4
3
2
1
1 2 3 4 5
L
I
KE
L
IH
O
OD
CONSEQUENCES
5
4
3
2
1
1 2 3 4 5
L
I
KE
L
IH
O
OD
CONSEQUENCES
2P
3S
4S6S
1S 2S
5S
January 5, 2007 THEMIS Mission Readiness Review 120
Accepted/Open Risks (Cont.)
ItemApproach
Risk ID
Status
Risk Description
5 A V0034
Condition: Delaminations have occurred within the Graphite Epoxy Motor (GEM) nozzles' Exit Cone Liners (ECL) and Throat Support Insulators (TSI). Consequence: Detrimental hot gas flow, adverse heating and eventual failure of the nozzle.
Risk accepted by LSP 8/10/05, (Ref ERB-02-085; ERB-01373KSC0; 01388KSC0; 02-245; 02-2).
6 M M0246
Condition: FM-14 2nd Stage tank assembly was found to have helium leakage from Oxidizer dome bracket at Decatur during fuel feedline leak checks. Membrane thinning due to aggressive sanding has concern as to whether there is acceptable membrane thickness in tank bracket locations.
Consequence: Mission loss or hazard to personnel due to failure of the 2nd stage tank assembly.
ERB to be held mid-Jan for Acceptance of Risks for THEMIS FM13 tankS = Safety & Mission Assurance Designator
P = LSP Designator
5
4
3
2
1
1 2 3 4 5
L
I
KE
L
IH
O
OD
CONSEQUENCES
5
4
3
2
1
1 2 3 4 5
L
I
KE
L
IH
O
OD
CONSEQUENCES
2P
3S
4S6S
1S 2S
5S
January 5, 2007 THEMIS Mission Readiness Review 121
Readiness Reviews
Review Date Location
Pre Vehicle On Stand (PreVOS) 03 January HB
MRR* 05 January GSFC
• Launch Vehicle Readiness Review (LVRR) 12 January KSC
• Safety & Mission Success 19 January HQReview (SMSR)
• Launch Site Readiness Review (LSRR) 01 February (est) KSC
• Flight Readiness Review (FRR) 12 February KSC
• Launch Mgmt. Coordination Meeting (LMCM)/ 13 February KSC Mission Dress Rehearsal (MDR)
• Launch Readiness Review (LRR) 14 February KSC
* Normal sequence of reviews is to conduct the Launch Vehicle Readiness Review before the SC MRR. Any updates will be captured in the LVRR package.
January 5, 2007 THEMIS Mission Readiness Review 122
Schedule, Range andLaunch Site Status
January 5, 2007 THEMIS Mission Readiness Review 123
Launch Site Schedule2006 2007
December January February
1/2/07
Name
12/21 2/2Upper Stage
PAF Mate Preps
PAF Mate to Motor
S/C Sep Connections
S/C Weigh Preps
Balance PAM
S/C Weigh
Preps for Motor Mate
Clampband Installation
Third Stage/Spacecraft Mate Preps
Third Stage Closeout
Transfer Third Stage to Astrotech
Spacecraft Mate
Spacecraft Finaling
Spacecraft Finaling (S/C Ops)
Engineering Walkdown
Third Stage and S/C Can-up & Transfer Preps
Third Stage and S/C Transport to Pad1/29 2/15Pad 17B
Preps of MST & Second Stage for S/C Erection
S/C Payload to Blockhouse Ringout
S/C Erection Preps
THEMIS S/C Erection
Spacecraft Functional Test
Spacecraft Launch Rehearsal
Flight Program Verification
Fairing Installation Preps
Fairing Installation
Fairing Elect Conn
Fairing Strongback Removal
S/C Systems Testing
FRR
Second Stage Prop Load
Mission Dress Rehearsal (MDR)
Spacecraft Testing
LRR
Preps for MST Move
Spacecraft Power/Clock Recycle
Post Launch SecuringLAUNCH
12/21 2/2
12/21
1/2
1/10
1/12
1/12
1/13
1/15
1/16
1/24
1/25
1/26
1/29
1/30
1/30
1/31
2/1
2/2
1/29 2/15
1/29
1/29
2/2
2/2
2/3
2/5
2/6
2/7
2/8
2/8
2/9
2/12
2/12
2/13
2/13
2/14
2/14
2/14
2/15
2/15
2/15
January 5, 2007 THEMIS Mission Readiness Review 123
January 5, 2007 THEMIS Mission Readiness Review 124
Eastern Range Operations Schedule
Jan/Feb/Mar 2007
X Range Configuration / Range Conflict \\ Additional Launch/Landing Attempt(s) HOLIDAY \ Configuration Hold
SUN MON TUE WED THU FRI SAT
4 5 6
15 16 17
18 19 22 23 24
25 26
3
7 109
20
1 228 3
313028
21
2
8
1211
1
HOLIDAY
JANUARY 29 FEBRUARY
27
Delta IITHEMIS
MARCH
13 14
January 5, 2007 THEMIS Mission Readiness Review 125
THEMIS Documentation Status
• Requirements Documentation Status
– All requirements documentation in place to support THEMIS
processing (Launch Site Support Plan [LSSP], Program
Requirements Document [PRD], Operation Requirements [OR]).
• Safety Documentation Status
– Missile System Pre-Launch Safety Package (MSPSP) – Approved.
– Hazardous procedure review and approval.
– 4 spacecraft standalone hazardous procedures for Pad operations.
• Launch Site Integration and Astrotech processing activities on
track to support February 15, 2007 Launch Date.
January 5, 2007 THEMIS Mission Readiness Review 126
Special Attention Items
January 5, 2007 THEMIS Mission Readiness Review 127
Engineering Review Board (ERB) /Engineering Review Summary (ERS)
• 19 ERBs Remain Open, expected closure by January 31, 2007.
• 75 ERSs Remain Open, expected closure by February 7, 2007.
• All mission ERBs must be closed before the FRR. Mission ERSs can be open at the time of launch.
Number of OPEN ERBs
Number of OPEN ERSs
Mission 1 13
Core/Fleet 18 62
TOTAL 19 75
• Due to the sequence of the reviews, there are a large amount of ERBs and ERSs open at MRR.
• Many of these ERBs and ERSs will be closed shortly after the PreVOS and Launch Vehicle Readiness Review.
January 5, 2007 THEMIS Mission Readiness Review 128
THEMIS Third Stage Confined TLX (CTLX)
• Boeing notified LSP of a TLX LAT failure in a lot of new-design (generally referred to as "Gen-2") lines that occurred at UPCO, the TLX vendor.
• Investigation showed that the failure mechanism was the formation of a "powder plug" in the line that interrupted propagation of the ordnance impulse.
• Direct cause was identified by Boeing to be:– Relatively insensitive explosive due to large explosive grain size
• Root cause was identified as: – Inadequate manufacturing/processing equipment – Ball milling process was inconsistent, permitted large grains to remain in milled powder – Inadequate inspections after ball milling did not properly characterize grain size
• Two lots are now suspect for the direct and root causes:– 608792-0J
» Lot used in units with LAT failure
– 60892-2B – lot used for THEMIS CTLX» The 2B lot has successfully completed LAT with no failures
• If lot separation can be demonstrated, then the currently installed CTLX lines could be used for the THEMIS mission.
January 5, 2007 THEMIS Mission Readiness Review 129
THEMIS Third Stage Confined TLX (CTLX) (Cont.)
• LSP convened a joint ERB 06-358 on December 20, 2006 to address flightworthiness impacts to the TLX and CTLX lots assigned to THEMIS.
– The TLX lines on the THEMIS vehicle were manufactured using a prior powder batch that was delivered with the desired grain size distribution and required no additional milling. Therefore, the TLX on the THEMIS vehicle is not suspect.
– Evaluation of the milling records and particle size distribution analysis data for each batch showed evidence that the milling procedure was not sufficiently specific to control the particle size distribution to the expected degree.
– The same data also convincingly showed that the batch used in the manufacture of the THEMIS CTLX lines was successfully milled to the desired size distribution, comparing very well with the prior batch of powder that required no milling.
– The milling records also provided sufficient data to recognize that the milling for 2B lot was set up differently than for 0J lot.
– All of 2B lot was milled in a consistent manner, all of 0J was milled in a consistent manner, but 2B lot was not milled like 0J lot .
• The ERB cleared the lines for THEMIS with no increased risk.
January 5, 2007 THEMIS Mission Readiness Review 130
• LSP was notified by Boeing that leaks were found at bracket weld of THEMIS’s second stage tank (FM14).
• Boeing reassigned tank FM11 to replace FM14 for the THEMIS Mission.
– During X-ray review, cracks were identified at the aft dome fuel feed line support bracket of FM11.
– Tank FM11 was de-assigned from THEMIS and Boeing reassigned the Orbview tank FM13.
• FM13 was inspected and evaluated at Decatur by the same NDE methods used for clearance of FM9 for STEREO.
• The dis-assembly of the FM14 tank was completed and re-assembly of the new THEMIS Second Stage (FM13) is completed and shipped to the Cape for processing.
Second Stage Tank
January 5, 2007 THEMIS Mission Readiness Review 131
• ERB 06-284-2 was conducted November 02, 2006 to determine the
flightworthiness of FM13 for THEMIS.
– The ERB assigned several action items that need to completed
before acceptance of the tank could be given.
– The actions generated during the review are currently being
worked and are expected to be closed by mid-January.
• A reconvene ERB 06-284-3 will be conducted to give
flightworthiness for FM13 in mid-January.
Second Stage Tank (Cont.)
January 5, 2007 THEMIS Mission Readiness Review 132
Separation Sequencing System (SSS)
LV Firing Signal to the SSS (2 places)
• Standard clampband boltcutters at the LV to SC interface replaced with 4 port manifolds on the probe carrier (2 places).
• Top Probe “A” separated first, then 3 sec later, 4 remaining Probes “B-E” are separated.
• GSFC provided SSS initiated by the DII upper stage event sequencing system (ESS).
• Manifolds incorporate output to ordnance initiated switches to confirm separation signal received at the LV to SC interface plane.
January 5, 2007 THEMIS Mission Readiness Review 133
Additional Pyro Switches
January 5, 2007 THEMIS Mission Readiness Review 134
Probe Separation Monitor System
• Probe separation to be monitored by Launch Vehicle Third Stage Telemetry System, channel FM12.
• Launch Vehicle provides 28 VDC from Third Stage Telemetry control box to Probe Carrier.
• Separation breakwires used on each individual Probe.
• Voltage divider network produces 32 distinct output voltages (0-5 VDC) for all possible separation scenarios.
• Probe Carrier to Third Stage Telemetry System Side-by-Side test completed successfully at Kennedy Space Center (KSC) on December 14, 2006.
• All output voltages met tolerance specified in the procedure and the system met the Interface Control Document (ICD) requirement that output voltages differ by greater than 3%.
January 5, 2007 THEMIS Mission Readiness Review 135
Summary
• NASA Launch Services Program is ready for continued THEMIS
launch vehicle processing.
• NASA Launch Services Program will complete all required
open work prior to approval for start of spacecraft mate
activities (LSRR - February 1, 2007 est.).
January 5, 2007 THEMIS Mission Readiness Review 136
Safety & Mission Assurance
Ronald Pierson
Explorers Systems Assurance Manager
January 5, 2007 THEMIS Mission Readiness Review 137
Mission Assurance Status
Safety documents are complete – supporting activities at Astrotech
GSFC has at least 1 SMA person at Astrotech throughout for surveillance of launch activities
Support of paperwork closure (PFRs, as-run procedures, Waivers, RFAs) is ongoing as work progresses
As-built vs. as design parts and materials lists have been completed; no outstanding issues
GIDEP Alerts are reviewed as issued (~95% closed)
Safety and Mission Success Review (SMSR) is scheduled for 1/19/07 at HQ
January 5, 2007 THEMIS Mission Readiness Review 138
System Safety
Final MSPSP - Approved by NASA Explorers, KSC, and Range Safety. KSC approval memo granted permission to arrive at the launch site processing facility on 11/28/06. No expected liens against transport to the launch pad.
Service Valve Waiver - RCS fill and drain valves are not 2-fault tolerant against inadvertent hydrazine leakage. Waiver processed to document non-compliance and additional controls implemented to protect personnel. Specifically, additional localized leak detection will be implemented after fueling. Waiver has been reviewed and approved by GSFC and KSC management.
High Pressure Line Underproof - Small section of line on high pressure side of RCS not taken to correct proof pressure level. Additional testing was performed on 10 sample pieces using the same manufacturing and welding techniques to demonstrate strength margin. This section will not see flight levels until after RCS re-press on orbit. Noncompliance review conducted by GSFC Codes 300, 400, and 500 in Spring 2006 and controls were accepted. Underproof documented via a deviation and approved by 300, 400, and 500 on 12/7.
Mechanical and Electrical GSE tested and approved
Orbital Debris Analysis final report completed and submitted
January 5, 2007 THEMIS Mission Readiness Review 139
Quality Assurance
Mirror FOD P/FR - Concern that mirror piece potentially struck blanketed Probe 1 COPV tank during environmental testing. Visual Inspection of the blanket performed by UCB and GSFC QA; no scarring or damage found. Analysis performed by Explorers estimating worse case accelerations of mirror fragment during spin balance, loads not great enough to cause damage. GSFC Propulsion Branch briefed on results of inspection and analysis and confirmed an additional proof test at 1.5 MEOP would not be required. Tank taken to 1.1 MEOP for leak testing on 12/14 and is currently sitting at the flight pressure (1750 psi). P/FR closed.
Probe capacitor replacement due to polarity error in PWA installation. All affected capacitors replaced in all 5 Probes. Probes are now finishing their additional free run time requirements (350 hous) after which the P/FR will be closed.
January 5, 2007 THEMIS Mission Readiness Review 140
Ready to Support Launch
GSFC and UCB SMA team is fully staffed and well-coordinated, roles are fully understood
SAM concurs with project risk assessment
Project and Explorers is responsive to SMA concerns
Safety and Mission Assurance is ready to support launch
January 5, 2007 THEMIS Mission Readiness Review 141
Safety & Mission Assurance
BACKUP
January 5, 2007 THEMIS Mission Readiness Review 142
Assurance/Technical Authority Activities
Status Summary Residual Risks
Quality Assurance
Software Complete Software assurance is complete None
Hardware Problems/PRs Ongoing PFRs are being addressed as opened See Systems Section
Alerts 98% + CompleteAll GIDEPS have been assessed and impacts
understood, reviewing as issuedNone
Quality Assurance Surveillance Ongoing Launch site surveillance ongoing None
Reliability/Maintainability
FMEA/CIL CompleteAnalyses completed Swales, reviewed by GSFC
Code 302 and suppliersSee Systems Section
Reliability Assessment CompleteAnalyses completed by Swales, reviewed by GSFC
Code 302 and suppliersSee Systems Section
Limited Life Items Complete Tracked for observatory by GSFC Systems None
Safety
Safety Data Package Complete Controls in place and verification complete. None
Contingency Planning Complete Contingency plans in place None
Range Safety Complete MSPSP Approved None
NASA Safety Reporting System Complete Close calls are closed None
SMA Integrated Activities
Training Complete All certifications and training in place None
Lessons Learned Review Complete Will enter into LLIS after launch None
Risk Management Ongoing Risk discussed as open and residual See Systems Section
Waivers/Deviations/Exceptions Complete Class I and II waivers complete None
January 5, 2007 THEMIS Mission Readiness Review 143
GSFC Project Role per the THEMIS Surveillance Plan
THEMIS Project Surveillance Plan has been released and implemented• Contract with UC Berkeley was executed for Phases B-E for the
development of the THEMIS spacecrafts and instruments. – Requirements and specifications contained in the contract,
statement of work, and referenced documents establish the baseline.
• The contract is cost type with government Insight. Insight has included:
– MRB– FRB– Inspection– PMPCB– Weekly reporting to GSFC
January 5, 2007 THEMIS Mission Readiness Review 144
GSFC Mission Assurance Role for Spacecraft
Spacecraft Development at Swales• Product Assurance Implementation Plan via CDRL • Government Source Inspection monitored by
GSFC QA• Software development monitored by GSFC
Software Quality Assurance• Roles and responsibilities:
– Clean room integration monitored by Swales QA team with GSFC surveillance at critical points
– Participation in Failure Review Boards at Probe s/c level,
January 5, 2007 THEMIS Mission Readiness Review 145
GSFC Mission Assurance Role for Instruments
Instruments - University of California Berkeley• Requirements levied via Product Assurance
Implementation Plan• Supplier Assurance Contract Assessment
performed post CDR• GSFC insight and in-plant Quality Assurance
representative starting at Probe I&T• Participation in Review Boards for parts, materials
and anomalies• Design reviews conducted by Independent Review
Team
January 5, 2007 THEMIS Mission Readiness Review 146
System Safety
Hazards• Controls are in place and verified for all hazards at ASO and
Pad• All hazards signed and residual risk accepted by program
management Procedures for field operations
• Reviewed all mechanical procedures• Reviewed all electrical and I&T procedures• Reviewed all propellant loading procedures
Status of safety documentation• MSPSP approved by Range• All Forms submitted and approved
January 5, 2007 THEMIS Mission Readiness Review 147
Orbital Debris Assessment
Orbital Debris• Final Orbital Debris Assessment (ODA) submitted on 17 Feb
2006 to NASA HQ.• THEMIS is non-compliant to Paragraph 4-2 for complete battery
discharging. Waiver letter being developed.• Delta II is non-compliant. This is a continuing issue.
Recommend Approval of THEMIS for Orbital Debris with waivers for ODA as noted above.
January 5, 2007 THEMIS Mission Readiness Review 148
Independent AssuranceActivities
Evaluation Area Status Residual Risks
1.SAC Assessment at Swales Complete None
2. SAC Assessment at UCB Complete None
3.IV&V Assessment of Spacecraft Software
Complete None
THEMIS IIRT System Reviews conducted in accordance with Systems Review Plan. Board Members invited to participate in Peer Reviews.
January 5, 2007 THEMIS Mission Readiness Review 149
Waivers
• No waivers to Level 1 Requirements
January 5, 2007 THEMIS Mission Readiness Review 150
New Lessons Learned
Lesson Description/Recommendation Applicability
1.Review PWB silkscreen to engineering drawing to verify polarity specific parts orientation
ID and Verify PWBs for polarity specific parts orientation
All missions
January 5, 2007 THEMIS Mission Readiness Review 151
SMA Responsibility Matrix
GSFC SMA Independent (GSFC
Code 301)
IV&V Contractor’s Representative
In-Plant or Itinerant Representative
External Review
Overall Mission Assurance
Ronald PerisonGSFC 301-286-4649
Rick PfistererGSFC QE301-286-7866
Mark GoansGSFC
Judith ConnellyIV&V Facility304-367-8314
N/A N/A Brian Keegan
Spacecraft Ronald PerisonGSFC 301-286-4649
Mark GoansGSFC
Judith ConnellyIV&V Facility304-367-8314
N/A N/A Brian Keegan
Instruments Ronald PerisonGSFC 301-286-5817
Mark GoansGSFC
N/A Jeremiah TolbertRon Hallet
Brian Keegan
January 5, 2007 THEMIS Mission Readiness Review 152
SMA Responsibility Matrix (2)
GSFC SMA Independent (Code 301)
IV&V Contractors Representative
In-Plant Representative
External Review
Parts Joseph OscheGSFC301-286-3306
Mark Goans N/A N/A N/A Brian Keegan
Materials Fred GrossGSFC301-286-8349
Mark Goans N/A N/A N/A Brian Keegan
Safety Jamie BurgetGSFC301-286-7852
Mark Goans N/A N/A N/A Brian Keegan
Reliability Nino IngenariGSFC301-286-6425
Mark Goans N/A N/A N/A Brian Keegan
Software Cindy Taylor301-286-7763
Mark Goans N/A N/A N/A Brian Keegan
January 5, 2007 THEMIS Mission Readiness Review 153
GSFC Code 300“Watch List”
Item # Description Reply Status Comments
97-01 Optocouplers - SETs. Impact
The Amptek, HV601B (ESA instrument) and the Micro pack 66099-300 (LVPS and PCB instruments) are used. "THEMIS has screened devices … suitable ..."
99-01 Actel FPGAs: NA-046 ImpactStart-up rules are being followed. LASP and Orbital have consulted Actel."THEMIS is employing … recommendations
99-02 Vishay - Metal Foil Resistors. No impactThe Vishay, RNC90Z (MIL-PRF-55182/9), established reliability resistors are used.
99-03 SpecTran - Fiber Optic Cable. No impact Not used
99-04 Bell Labs - Up-screened diodes. No impact Not used
99-05 ATC Capacitors: NA-048. No impact Not used
00-01 Interpoint: MT2-P-00-01. No impact Not used
01-01 Advanced Analog: DC-DC converters. No impact Not used
02-01 ACS Polarity Verification. Impact “Swales has provided polarity verification plan."
03-01 Metropole: Diplexer anomaly. No impact Not used
04-01 Hitachi EEPROM: bit flips. Impact
The Maxwell EEPROM (5962-3826719Q7C, 28C011TRPFB-12) is used in the DCB instrument and has the Hitachi die. Reviewed and risk accepted.
04-02 cPCI Connector Qualification. No impact Not used
04-03 TRAK Microwave: Isolator. No impact Not used
05-01 Emcore: Solar Cell Welds. No impact Not used
05-02 Starsys: Qwknut. No impact Not used
January 5, 2007 THEMIS Mission Readiness Review 154
GSFC Code 300“Watch List” (2)
Item # Description Reply Status Comments
05-03 ARDE Overwrapped COPV No impact Not used
05-04 Goodrich Star Tracker No impact Not used
05-05 Photography Impact
"There are no contractual requirements for photography/video in the … THEMIS …. Contract". However Swales and Berkeley have been performiong photography as part of standard practice.
05-06Ball Aerospace – Conformal Coating No impact Not used
05-07Trompeter Electronics - Connector. No impact Not used
05-08 LoDs:DCMC Workmanship Certs. No impact Not used
05-09Conax Florida Corporation - Pyrovalves. No impact Not used
05-10 Actel RTAX FPGAs.No impact
All contractors are applying power to these parts. It is the intent to acquire at least 1000 hours on each device prior to shipment. All time is being recorded. DPAs have been performed to each lot date code.
05-11 PK Selective - Unauthorized Paint.Yes, impact Approved per the PMPCB. "… the instruments have
passed all outgassing requirements …"
06-01RAD750 EEPROM Vibration Failure.
No impact Not used
January 5, 2007 THEMIS Mission Readiness Review 155
Software IV&V
Judith Connelly
THEMIS IV&V
January 5, 2007 THEMIS Mission Readiness Review 156
Outline of Content
• Summary of IV&V tasks and recommendation• Summary of Project Accepts Risk (PAR) Issues• Conclusion• Backup Slides
Backup Contents:
Summary of All Issues generated, resolved & closedDetail on Two Programmatic Risks –(status closed )List of Artifacts AnalyzedBAU issues breakdown by FunctionIDPU issues breakdown by FunctionSeverity Definitions
January 5, 2007 THEMIS Mission Readiness Review 157
Summary of IV&V Tasks and Recommendation
The goal of IV&V work on THEMIS is to verify and validate that THEMIS FSW will support mission success. Towards that end IV&V performed analysis on Spacecraft Flight Software Bus Avionics Unit (BAU) and Instrument Data Processing Unit (IDPU) Software in the following areas:
Requirements Analysis : To confirm that system and software requirements are complete, consistent, traceable and testable.
Design Analysis: To verify software design models and algorithms provide implementation of associated requirements and handle off-nominal functionality.
Code Analysis: To verify that code is free of implementation errors and that it fulfills the requirements.
Test Program Analysis : To verify test artifacts cover all requirements levied on the software; to verify test results were expected; To confirm that testing demonstrated that the software performs reliably under realistic scenarios.
Based on the results of these analyses, issue closures and the acceptance of risk by the Project of technical issues not resolved, IV&V has no significant concerns regarding
the operational readiness of the THEMIS spacecraft FSW.
IV&V has completed limited analyses of the Ground System, including analysis of the GSICD, Mission Ops and Flight Ops artifacts. No significant issues were found as a
result of these analyses.
IV&V recommends THEMIS for launch.
January 5, 2007 THEMIS Mission Readiness Review 158
Project Accepts Risk (PAR) TIMs Summary
PAR TIMs (Technical Issue of Memoranda) state means that the Project recognizes that IV&V has some outstanding concerns with an issue and that the Project accepts risk, if any, associated with that issue. In
accepting this risk the Project does not necessarily agree nor disagree with the issue itself. These TIMs have not been closed.
The Project has demonstrated a workaround to the core issues identified in the TIMs.There are 13 PAR TIMs supporting the 3 impact statements below.
IV&V concurs that there is a low likelihood of occurrence and that these are acceptable risks.
Impact: Data Storage writes could be corrupted by a process interrupt, and THEMIS could be left in an incoherent state. THEMIS could fail to respond to time-critical events. Data quality may also be degraded.
Specific area: Data Storage and Checksumming, Semaphore lock/unlock
Impact: There is a potential for unexpected behavior of unused objects and functions. Emergent behavior is unknown for 1) inconsistently defined macros and 2) variables that are defined more than once. Untested return values could cause unexpected interrupts or failure of process execution.
Specific area: Health & Safety, General, Boot
Impact: Possible degradation of timing for probe stored command execution.Specific area: Stored Commands
January 5, 2007 THEMIS Mission Readiness Review 159
IV&V Conclusion
Based on the results of these analyses, issue closures and the acceptance of risk by the Project of technical issues not
resolved, IV&V has no significant concerns regarding the operational readiness of the THEMIS spacecraft FSW.
IV&V has completed limited analyses of the Ground System, including analysis of the GSICD, Mission Ops and Flight Ops artifacts. No significant issues were found as a result of these
analyses.
IV&V recommends THEMIS for launch.
January 5, 2007 THEMIS Mission Readiness Review 160
Backup
•Summary of All TIMs generated, resolved and closed•Detail on Two Programmatic Risks (closed )•List of Artifacts Analyzed•BAU TIM breakdown by Function•IDPU TIM breakdown by Function•Severity Definitions
January 5, 2007 THEMIS Mission Readiness Review 161
All TIMs are closed with the exception of Project Accepts Risks (PAR) TIMs as previously outlined.
No formal TIMs were generated for the Ground System. Informal reports were delivered to the project with
recommendations.
Summary of All Technical Issues of Memoranda (TIM) generated, resolved & closed
BAU IDPU System TotalRequirements 84 18 12 114
Design 7 50 N/A 57Code 58 0 N/A 58Test 125 6 N/A 131
Traceability 23 32 N/A 55
Total 297 106 415
January 5, 2007 THEMIS Mission Readiness Review 162
Programmatic Project Risks
BAU Testing - Closed September 06IF the BAU test artifacts do not confirm traceability to all BAU
FSW requirements THEN there is no confirmation that all BAU FSW requirements have been completely and adequately tested. Closure Comments: The dialogue with the project has resolved many testing TIMs. This dialogue will continue until testing artifacts have been shown to contain the required traceability. The original driver for the risk has been mitigated.
Configuration Management - Closed June 06
IF the reallocated requirements identified in the Comments and ResChron sections of this Risk TIM are not adequately documented and controlled at the system level, THEN the receiving subsystem may not fully understand the intent and therefore may not properly implement the requirement. Closure Comments: “Through analysis of artifacts and discussion with the Project, IV&V has been able to verify that the Project does utilize their formal SCN process for requirements deletions and changes.
January 5, 2007 THEMIS Mission Readiness Review 163
Artifacts Reviewed
BAURequirements• FSW SRS Revs 1.1, 2.0, 2.2, 3.0 • Flight Software User’s Guide v1.0 • Boot SRS Revs 1.0, 2.1, 2.2
Design• BAU CDR Presentation (6/15/04)
Code• FSW Build 2• FSW Build 2.504• FSW Build 3.003• FSW Build 3.1 • FSW Build 3.19• Boot Build 0• Boot 2.510
Test• BAU FSW Build 2• BAU FSW Build 3.000/3.003/3.10 • BAU FSW Build 2.504 CPT• BAU FSW Test Plan v1.0
IDPURequirements• SRS Revs D, E, F
Design• THEMIS IDPU FSW Design document
Code• IDPU FSW Phase 1.04• IDPU FSW Phase 2.01• IDPU FSW Phase 3.03• IDPU FSW Phase 4
Test• IDPU CPT Plan
Ground• GS artifacts analyzed:• THM-SYS-013, THEMIS Mission Ops Plan, 10/3/06• THM-SYS-018, THEMIS Flight Ops Plan, 9/29/06• THM-SYS-117, THEMIS GS ICD, 10/3/06• • Ground artifacts reviewed:• THM-SYS-117, THEMIS GSICD, 11/20/06• • Ground artifacts TO BE ANALYZED:• THM-SYS-117, THEMIS GSICD, Final (Date TBD)
SystemRequirements• MRD Revs C, D, E, F, G, H
Below is a list of THEMIS artifacts which IV&V has reviewed.
January 5, 2007 THEMIS Mission Readiness Review 164
All BAU TIMs by severity and function
1 2 3 4 5 Total Issue CountBoot 0 1 58 3 8 70
Bus Avionics Manager 0 0 3 0 0 3Checksumming 0 0 7 0 1 8
Command Processing 0 2 28 4 1 35Data Storage 0 0 30 0 0 30
General 0 1 27 5 1 34Health and Safety 0 0 4 1 0 5IRU Processing 0 0 0 0 0 0Limit Monitoring 0 0 1 1 0 2
Memory Management 0 1 13 4 0 18Stored Command Processing 0 0 26 0 0 26Sun Sychronous Processing 0 0 17 0 0 17
Telemetry Processing 0 0 33 3 1 37Thruster Firing 1 6 1 0 0 8
Time Code Processing 0 0 3 0 0 3Total Issue Count 1 11 252 21 12 297
All States Included and Parsed with Saved Query: BAU CFL MRR
Severity
January 5, 2007 THEMIS Mission Readiness Review 165
All IDPU TIMs by severity & function
1 2 3 4 5 Total Issue CountAttitude Control 0 0 0 0 0 0
Background 0 0 2 0 0 2Burst Triggering 0 0 0 0 0 0
Commands 0 0 4 2 0 6Compression algorithms 0 0 2 1 0 3
EFI Deployment 0 1 4 0 1 6EFI FGM Fit Manager 0 0 4 0 0 4
EFI Manager 0 0 18 4 1 23ETC Manager 0 0 2 0 0 2
Executive 0 0 5 1 0 6Fast Floating Point 0 1 0 0 0 1
FGM Manager 0 0 2 0 0 2General 0 0 2 0 0 2
Housekeeping 0 0 4 1 0 5Input/Output 0 0 3 2 0 5
Loader 0 0 2 0 0 2Matrix Solver 0 0 1 0 0 1
Power Manager 0 0 8 0 0 8SCM Manager 0 0 4 0 0 4
Spin Fit Calculator 0 0 5 0 0 5SSR Manager 0 0 5 2 0 7
Telemetry 0 0 5 0 0 5Trigonometrics 0 0 0 0 0 0
Utilities 0 0 5 1 0 6Total Issue Count 0 2 88 14 2 106
All States Included and Parsed with Saved Query: IDPUCFL MRR
Severity
January 5, 2007 THEMIS Mission Readiness Review 166
TIM Severity Definitions
*IEEE J-STD-016-1995 definitions are used.
1 a) Prevent the accomplishment of an essential capability b) Jeopardize safety, security, or other requirement designated critical.
2 a) Adversely affect the accomplishment of an essential capability and no work-around solution is known b) Adversely affect technical, cost or schedule risks to the project or life cycle support of the system, and no work-around solution is known
3 a) Adversely affect the accomplishment of an essential capability but a work-around solution is known b) Adversely affect technical, cost, or schedule risks to the project or life cycle support of the system, but a work-around solution is known
4 a) Result in user/operator inconvenience but does not affect a required operational or mission essential capability b) Result in inconvenience for development or maintenance personnel, but does not affect the accomplishment of these responsibilities
5 Any other affect
January 5, 2007 THEMIS Mission Readiness Review 167
Integrated Independent Review Team
Mark Goans
GSFC Systems Review Office
Brian Keegan
Independent Consultant
January 5, 2007 THEMIS Mission Readiness Review 168
Integrated Independent Review Approach
• Major technical and programmatic reviews were conducted per the “THEMIS Integrated Independent Review Plan”, dated July 29, 2004.
Modifications from that plan were minor, being associated only with the S/N of the bus ship sequence from Swales and the conduct of a Delta-PSR telecon prior to shipment of the flight segment from JPL to KSC.
A series of Engineering Peer Reviews were held by UCB Project Management preceding both Mission PDR and Mission CDR. Results were provided to and reviewed by the IIRT in conjunction with the Mission PDR & CDR Reviews.
January 5, 2007 THEMIS Mission Readiness Review 169
Integrated Independent Review Team (IIRT) Members
–Mark Goans GSFC [Systems Review Office] (Co-chair)–Brian Keegan Independent (Co-chair)–Bill Taylor Independent - Project Mgt., Systems–Frank Martin Independent - Science, Instruments–J. B. Joyce Independent - Operations–Terry Ford Independent - GN & C–Rick Schnurr GSFC - Electrical Systems–Alan Posey GSFC - Mechanical Systems–Lou Fantano GSFC- Thermal –Scott Glubke GSFC - Propulsion–Ed Gaddy GSFC - Power–Ronnie Killough SWRI - Software
January 5, 2007 THEMIS Mission Readiness Review 170
Mission Operations Review Team Members
-Mark Goans, GSFC [Systems Review Office] (Co-chair) -J.B. Joyce Independent (Co-chair) -Mary Foote CSC, IT Security-Steve Cooley GSFC, Flight Dynamics-Patrick Crouse GSFC, Space Science Mission Operations-John Jackson GSFC, Space-Ground Interface-John Donohue GSFC, Command and Control -Rob Messerly Titan, Mission Readiness Testing -Madeline Butler GSFC, Engineering-Bob Wiegand GSFC/Flight Dynamics Systems-Stan Scott GSFC/Science Data Processing-Glen Miller HTSI, Flight Operations-Emil Kirwan HTSI, Reliability Engineering
January 5, 2007 THEMIS Mission Readiness Review 171
Flight Operations Review Team Members
-Mark Goans, GSFC [Systems Review Office] (Co-chair) -J.B. Joyce Independent (Co-chair) -Madeline Butler GSFC - Engineering -Paul Garza GSFC - Space/Ground Interface -Pat Johnson GSFC - Flight Dynamics Systems-Emil Kirwan HTSI - Reliability Engineering -Ben Lui GSFC - Command and Control -Maureen Madden GSFC - Space Science Mission Ops -Conrad Schiff GSFC - Flight Dynamics -Stan Scott GSFC - Science Data Processing
January 5, 2007 THEMIS Mission Readiness Review 172
THEMIS IIRT Reviews
Element Review Date
Mission
SRRJuly 8-9,
2003
PDRNov. 12-14,
2003
CDRJune 17,
2004
MORMarch 7-8,
2005
P2 PERMarch 16,
2006
P1,3,4,5 PERJune 23,
2006
FOROct. 4-5,
2006
PSR Oct. 26, 2006
Delta-PSR Dec. 5, 2006
Element Review Date
Payload
PDR @ MPDR
CDRJune 16,
2004
Test Summary
Dec. 9, 2004
F #1 PER May 2, 2005
F #1 PSRSept. 21,
2005
F #2,3 PERAug. 27,
2005
F #2,3 PSRNov. 10,
2004
F #4,5 PERNov. 10,
2005
F #4,5 PSR May 5, 2006
Element Review Date
Spacecraft
PDR Oct. 29-30, 2003
CDR June 14-15, 2004
Test Summary
April 5, 2005
Bus #2 PSR Nov. 17, 2005
Bus #3 PSR March 23, 2006
Bus #4 PSR May 4, 2006
Bus #1 PSR May 31, 2006
Bus #5 PSR June 12, 2006
Carrier PSR May 31, 2006
January 5, 2007 THEMIS Mission Readiness Review 173
THEMIS RFA Summary
0
10
20
30
40
50
60
Inst
. CD
RF1
PER
F1 P
SR
F2,3
PE
RF2
,3 P
SR
F4,5
PE
RS
/C P
DR
S/C
CD
RB
us 2
PSR
Bus
3 P
SRB
us 4
PSR
Bus
1 P
SRB
us 5
PSR
S
RR
PD
RC
DR
MO
RP
2 P
SRP
1,3,
4,5
PER
FOR
PSR
Del
ta-P
SR
RFAs Complete / Concurred (Total = 267)RFAs Complete / Not Concurred (Total = 2)
January 5, 2007 THEMIS Mission Readiness Review 174
Key Project Management Practices
Legend: Green - To date, activities are fully compatible with good practice for similar successful projects. Yellow - To date, activities exhibit weakness that warrants change to control risk. Red - To date, activities are deficient and immediate corrective action is essential to minimize risk.
Key Management Practice SRR PDR CDR PER PSR
Organization & Communication
Systems Management
Safety
Risk Management
Mission Assurance
Integration TBD
Verification TBD
Operations
Engineering Peer Reviews TBD
Independent Reviews
January 5, 2007 THEMIS Mission Readiness Review 175
THEMIS Residual Risk Rating
LIKELIHOOD
(0.1% <PT < 2%) (PS < 10-6)Very Low1
(2% < PT < 15%) (10-6 < PS < 10-3)Low2
(15% < PT < 25%) (10-3 < PS < 10-2)Moderate3
(25% < PT < 50%) (10-2 < PS < 10-1)High4
(PT > 50%) (PS > 10-1)Very High5
Technical SafetyLevel
CONSEQUENCE
1
2
3
4
5
Level
No impact to full mission success criteria
Minor impact to full mission success criteria
Moderate impact to full mission success criteria. Minimum mission success criteria is achievable with margin
Major impact to full mission success criteria. Minimum mission success criteria is achievable
Minimum mission success criteria is not achievable
TECHNICAL
Negligible or No impact.
Could cause the need for only minor first aid treatment .
May cause minor injury or occupational illness or minor property damage.
May cause severe injury or occupational illness or major property damage
May cause death or permanently disabling injury or destruction of property.
SAFETY
CONSEQUENCE
LIK
EL
IHO
OD
F D,E
B,C*A
THEMIS RISK MATRIX
Note: Numerical techniques were not used to estimate likelihood probabilities.
= Technical Rating*
January 5, 2007 THEMIS Mission Readiness Review 176
THEMIS Residual Risk Assessment
Item Risk Description Failure
LikelihoodFailure
Consequence
A For all probes, a segment of both the high and low pressure portions of the Hydrazine Propulsion System were not proof tested to 1.5 MEOP.
1 4
Rationale:Likelihood - All hardware components were proof tested to appropriate pressures. Only segments of the line welds were not properly tested. Separate testing of 10 sample welds burst at > 9 times the required THEMIS proof pressure. GSFC TA and safety as well as KSC safety has accepted the alternate approach.
Consequence - Loss of the RCS would cause loss of the associated probe. Full mission science can be accomplished with four probes.
January 5, 2007 THEMIS Mission Readiness Review 177
THEMIS Residual Risk Assessment
Item Description Likelihood Consequence
B Set-point of thermostats in RCS secondary heaters is closer than desired to freezing temperature of hydrazine propellant.
2 1
Rationale: Likelihood - RCS design has fully redundant thermostat and heater circuitry. Primary RCS thermostat set points are above any threshold of hydrazine freezing concerns. Set point of secondary RCS thermostats is marginal. If primary RCS heaters fail, control of eclipse duration becomes required method of RCS temperature control.
Consequence - Long duration eclipses do not occur until 2nd year of operations. Baseline mission plan accomplishes full mission objectives in first year.
January 5, 2007 THEMIS Mission Readiness Review 178
THEMIS Residual Risk Assessment
Item Description Likelihood Consequence
C THEMIS uses four HLX6228TBR devices per BAU Data Processing Module (DPM) all of which use ramp time in the suspect range identified in the recent GIDEP Alert.
2 1(Technical)
Rationale: Likelihood - The DPM is powered up only once prior to launch and remains powered throughout launch and during all mission phases. There is no credible failure which power cycles the SRAM on orbit. There have been no SRAM errors during the hundreds of power-cycles of the flight hardware/software testing performed to date on the five flight probes and two engineering units. Part testing by the manufacturer has shown behavior of affected devices (~ 3%) to be consistent over time. Screening recommended by Alert to 2x application ramp time was not possible however because devices had been already installed.
Consequence - Technical consequence to achieving mission objectives is negligible given that launch will not have occurred upon discovery of the problem. A power recycle of the affected probe could be attempted. In the worst case, potentially significant cost and schedule implications could result.
January 5, 2007 THEMIS Mission Readiness Review 179
THEMIS Residual Risk Assessment
Item Description Likelihood Consequence
D Potential failure of AMPTEK A121 devices in ESA instrument cannot be ruled out given failure of device in same lot due to shorting effects of silver dendrite growth.
1 2
Rationale: Likelihood - GSFC recommended RGA, DPA, and life testing of residual devices from same lot has been completed with positive results.
Consequence - Failure of limited numbers of devices on orbit could be tolerated with minimum mission impact through reorienting attitude at which science measurements are made.
January 5, 2007 THEMIS Mission Readiness Review 180
THEMIS Residual Risk Assessment
Item Description Likelihood Consequence
E Solar Panel Qualification Panels were not subjected to a test of their output at maximum operating temperature.
1 2
Rationale: Likelihood - Array design of THEMIS is similar to C/NOFS except that THEMIS uses "strain relief" cell interconnects. (Note that cell interconnects were an element of the C/NOFS failure.) While the THEMIS qualification panel was not operated at its highest predicted operating temperature subsequent to thermal cycling exposure, the panel did have current passed through it during the test, which would have likely caught the most serious issues of open welds. All THEMIS flight panels were subjected to "Hot LAPS" testing after thermal vacuum exposure and were thus shown to be good at max operating temperature. A post-failure mechanical analysis of the array configuration by Aerospace modeled the C/NOFS failure. The same analysis of the THEMIS configuration showed positive margin.
Consequence - A single failure would result in 1/16 power loss which could be accommodated via duty cycling of instruments without significant effect on accomplishing mission science.
January 5, 2007 THEMIS Mission Readiness Review 181
THEMIS Residual Risk Assessment
Item Description Likelihood Consequence
F 100+ hour run time on EFI instrument since replacement of "reversed" capacitors has not occurred in T-V and is not likely to reach the 350 hour GSFC "rule" on failure-free operation.
1 1
Rationale: Likelihood - While not a formal requirement on THEMIS, the UCB approach complied with GSFC run time and failure free guidance except after replacement of reversed capacitors in the EFI Instruments. Single T-V cycle, 1 axis vibe, and > 100 hours of ambient operation has been successfully accomplished after rework. (Current planning will likely achieve ~200 hours.)
Consequence - Single "open" capacitor failure has essentially no impact because of redundant measurements on opposite sides of spinning spacecraft. Single "short" failure causes loss of measurement in one axis, thereby degrading timing resolution.
January 5, 2007 THEMIS Mission Readiness Review 182
Open IIRT Concerns
• None
January 5, 2007 THEMIS Mission Readiness Review 183
IIRT Conclusions
• All THEMIS residual risks are low and are acceptable.
• IIRT review of all unverified failures uncovered no residual risks of note.
• Flight predicted temperatures for all planned nominal and contingency cases are satisfactory.
• Satisfactory concurrence with response to remaining RFAs is foreseen based upon completion of discussions currently underway.
• THEMIS is ready to proceed with final launch preparations.
• Upon satisfactory completion of processing and closure of remaining RFAs, THEMIS is ready for launch.
January 5, 2007 THEMIS Mission Readiness Review 184
Public Affair Plan
Cynthia O’Carroll
GSFC Public Affairs Office
January 5, 2007 THEMIS Mission Readiness Review 185
Public Affairs Office (PAO) Responsibilities
• Goddard Space Flight Center (GSFC) - leads, plans and coordinates public affairs and outreach activities with NASA Headquarters and our partner organizations; prepares and distributes all media materials, including news releases, the mission press kit, the mission Web site and other mission specific products; organizes press briefings; coordinates Guest Operations.
• Mission Partners - lead: Space Sciences Laboratory at the University of California at Berkeley (UC Berkeley); International space agencies from Germany, Canada, France and Austria; and NASA JPL.
• Kennedy Space Center (KSC) - lead for photo/video documentation of spacecraft processing and launch vehicle buildup; coordinates the spacecraft press opportunity at Astrotech; coordinates the L-1 Press Briefing to be held at the KSC Press Site; arranges NASA TV support and live coverage of the briefings and the launch; and provides launch commentary.
• Swales Aerospace - built spacecraft bus and probe carrier; participates in PAO activities and supports Guest Ops.
• United Launch Alliance (ULA) - provides Delta II Launch Vehicle; participates in PAO activities and supports Guest Ops.
January 5, 2007 THEMIS Mission Readiness Review 186
PAO Responsibilities
• Press Kit
– THEMIS Fact Sheet
– THEMIS Lithograph
– Information on the instruments, the spacecraft bus, the probe carrier and the LV
– Other mission related products and images
– Press Kit will be available on the NASA Web site and in hardcopy
January 5, 2007 THEMIS Mission Readiness Review 187
PAO Responsibilities
• News Releases:
– Spacecraft Arrival - NASA HQ, KSC, GSFC, and UC Berkeley issued release on 12/11
– Weekly Status Reports - KSC; THEMIS and Delta II processing– General News Release - NASA HQ, GSFC and UC Berkeley; general info about
the THEMIS mission before the L-30 Press Briefing– Note-to-Editors - NASA HQ, KSC and GSFC; logistics for the Press Opportunity at
Astrotech– Pre-launch/Mission Science Briefing Release - KSC; logistics and info about NASA
TV coverage for the L-1 Press Briefing– Post-launch Status Reports - GSFC and UC Berkeley; issue a status report after
the successful launch– Science Results News Releases - NASA HQ, GSFC and UC Berkeley; coordinate
the timing and content of science results news releases with partners as necessary
January 5, 2007 THEMIS Mission Readiness Review 188
PAO Responsibilities
• NASA Television and Web Coverage:
– THEMIS Promo - GSFC TV has produced a brief animated video of the THEMIS launch and deployment with music.
– Video File - GSFC TV has produced a video file that will be broadcast live on NASA TV for the L-30 and the L-1 Press Briefings and on the day of the launch. The video file contains B-roll of spacecraft at Swales, UC Berkeley, JPL and KSC. It also contains science and spacecraft animation and interviews.
– Pre-launch Support - KSC will arrange TV support and coverage the L-1 Press Briefings at the KSC Press Site to be carried live on NASA TV.
– Launch Coverage - KSC will arrange live launch day coverage as well as the launch commentary. The launch will also be available on the NASA Web site.
– THEMIS Web Sites - http://www.nasa.gov/themishttp://sprg.ssl.berkeley.edu/themishttp://ds9.ssl.berkeley.edu/themishttp://www.swales.com/company/themis_contract.html
January 5, 2007 THEMIS Mission Readiness Review 189
PAO Responsibilities
• L-30 Press Briefing:
– Will be held by telecon and supported by the the mission Web site; NASA TV will air the THEMIS video file on the same day.
– Participants:• Moderator: George Diller, NASA KSC PAO• Craig Pollock, NASA HQ THEMIS Program Manager• Frank Snow, NASA GSFC THEMIS Mission Manager• Vassilis Angelopoulos, UC Berkeley THEMIS Principal Investigator• Peter Harvey, UC Berkeley THEMIS Project Manager
January 5, 2007 THEMIS Mission Readiness Review 190
PAO Responsibilities
• L-1 Briefings:
– Will be held on L-1 after the Launch Readiness Review at the KSC Press Site; will air on NASA TV with THEMIS video file.
– Pre-launch Briefing: • Moderator: George Diller, NASA KSC PAO• Richard R. Fisher, NASA HQ Director of Heliophysics Division• Frank Snow, NASA GSFC THEMIS Mission Manager• Peter Harvey, UC Berkeley THEMIS Project Manager• Chuck Dovale, NASA KSC Launch Director• ULA, Director of NASA Programs• U.S. Air Force Delta II Launch Weather Officer, 45th Weather Squadron
– Mission Science Briefing:• Moderator: George Diller, NASA KSC PAO• Craig Pollock, NASA HQ THEMIS Program Manager• David Sibeck, NASA THEMIS Project Scientist• Vassilis Angelopoulos, UC Berkeley THEMIS Principal Investigator
January 5, 2007 THEMIS Mission Readiness Review 191
PAO Responsibilities
• Outreach Activities:
Completed:– Spring 2006 AGU: Science Writers Workshop highlighting THEMIS science– November 2006: Media Training was provided to the PM, the PI and the PS as the
primary spokespersons for the mission. – September 2006 SpaceLink for Educators at the Maryland Science Center:
GSFC’s Dr. Sten Odenwald, a THEMIS E/PO Formal Education Partner, discussed the THEMIS Mission science and provided activities for teachers and tips on how to share them with students.
Planned:– April 2007: Dave Sibeck to present THEMIS at “About Goddard” seminar
Develop a feature presentation with SVS on Heliophysics for “Science on a Sphere”
– Space Chats at the GSFC Visitor Center– GSFC View, Dateline, Intranet, poster boards– Partner with public libraries for a Heliophysics speaker and special display of
related materials– Events/presentations at Maryland Science Center, Howard B. Owens Science
Center and other community venues
January 5, 2007 THEMIS Mission Readiness Review 192
PAO Responsibilities
• Education
– NASA GSFC:• July 2006 - NASA Explorer Schools Orientation Workshop and
Distance Learning Network Workshop with presentations of Heliophysics science and solar classroom activities
• March 2007 - Heliophysics Teacher Workshop for Stereo, THEMIS and AIM: science and classroom application activities using 3 new guides: “Exploring Magnetism”, “Exploring Magnetism in the Solar Wind” and “Exploring Magnetism in Solar Flares”
• Sun-Earth Day 2007/IHY - GSFC Visitor Center for local schools; theme is “Living in the Atmosphere of the Sun”
January 5, 2007 THEMIS Mission Readiness Review 193
PAO Responsibilities
– UC Berkeley:
• Geomagnetic Event Observation Network by Students (GEONS) in which 10 magnetometers are placed in (or associated with) 13 schools across the country; receive data from the mission; teaches about Earth’s magnetic field and its changes that are related to auroral substorm activity
• Professional development for teachers, with a focus on the Tribal Colleges• Planning to launch of a new Lawrence Hall of Science Great Explorations
in Math and Science (GEMS) site in Nevada• Creation and dissemination of a Space Telescope Science Institute
ViewSpace show on auroras and THEMIS• The THEMIS E/PO partnerships, methods, activities, and visibility are
monitored and evaluated by Cornerstone Evaluation Associates (CEA); yearly formative evaluation reports are receieved and action taken as necessary
• Publications: “Exploring Magnetism,” “Exploring Magnetism on Earth,” “The Northern Lights”
• Development and maintenance of a THEMIS E/PO Web site.
January 5, 2007 THEMIS Mission Readiness Review 194
PAO Responsibilities
• Post-Launch Events and Services:
– Contingency Press Briefing - If a launch contingency should occur, a briefing will be targeted for 2 hours after the contingency or as soon as significant information is available. Representatives from NASA, UC Berkeley, Swales and ULA will attend.
– GSFC Code-A-Phone and Web Page - Information regarding the THEMIS launch will be placed on the GSFC Code-A-Phone (301-286-NEWS) and on the GSFC Web page. KSC will also update their Code-A-Phone beginning on L-3.
January 5, 2007 THEMIS Mission Readiness Review 195
Guest Operations
• Guest Operations:
– NASA HQ in collaboration with GSFC, KSC, UC Berkeley, Swales and ULA
– Invitations mailed 4-6 weeks prior to launch– Guests are encouraged to visit the Guest Operations Web site to RSVP
and learn about updates to the schedule: http://guestops.hq.nasa.gov– Guest Operations typically include:
• Guest Check-in at the KSC Visitor Complex, beginning at L-1• Guest Briefing held on L-1• Transportation from Visitor Complex to launch viewing site • Guests monitor launch schedule via NASA toll-free phone hotline• Reception driven by contractor partners
January 5, 2007 THEMIS Mission Readiness Review 196
Readiness Statement
Frank Snow
Mission Manager
January 5, 2007 THEMIS Mission Readiness Review 196
January 5, 2007 THEMIS Mission Readiness Review 197
Summary
Summary Readiness to Proceed
Probes and Probe Carrier are Ready Plans and Procedures for Launch are Ready Mission Ops Center is Ready Ground Network Testing will be completed before 1/19/07 Ops Procedures & Personnel are Ready Ground Based Observatories are Ready Launch Vehicle – NASA LSP is ready for continued launch vehicle processing
Key Reviews Safety/Mission Assurance Review 1/19/07 Mission Readiness Board 1/23/07 Flight Readiness Review 2/12/07 Launch Readiness Review 2/14/07
January 5, 2007 THEMIS Mission Readiness Review 198
Acronyms
January 5, 2007 THEMIS Mission Readiness Review 199
M12. ACRONYMS LIST 3DP 3 Dimensional Plasma instrument on the WIND spacecraft A/D Analog-to-Digital Converter AA/OSS Associate Administrator for the Office of Space Sciences AC Alternatic Current ACE Advanced Composition Explorer ACS Attitude Control System ADC Analog to Digital Converter AEC-ABLE A company name AFRL Airforce Research Laboratories AGI Analytical Graphics Inc. AGO Automated Geophysical Observatory AGS Alaska Ground Station at Poker Flat AKM Apogee Kick Motor AKR Auroral Kilometric Radiation AMPTE US/European Mission consisting of 3 satellite: CCE, IRM and UKS AMSAT Amateur Radio Operator Satellite AO Announcement of Opportunity APER Argument of Perigee APID Application Process Identifier ASA Austrian Space Agency ASI All Sky Imager ASIC Application Specific Integrated Circuit ASCII American Standard Code for Information Interchange ATS Absolute Time Sequence AXB Axial Booms BAU Bus Avionics Unit
BEB Boom Electronics Board BGS Berkeley Ground Station (used for satellite tracking of FAST, HESSI, IMAGE and other spacecraft) BPSK Binary Phase Shift Keying BTE Bench Test Equipment BTS Bester Tracking Systems software C&DH Command & Data Handling C&T Command & Telemetry CAD Computer Aided Design CANOPUS A network of ground observatories (magnetometers, all sky cameras and meridional scanning photometers) in Canada Cassini European Spacecraft to Saturn CC Configuration Control CCAS Cape Canaveral Air Station CCD Charge-Coupled Device CCE A US / European Scientific Satellite CCI Cross Field Current Instability CCP Civil and Commercial Program CCSDS A signal encoding procedure outlined by NASA’s Consultative Committee for Space Data Systems CD Current Disruption CDAW Community Data Analysis Workshop A substorm event-based forum CDHS Command & Data Handling Subsystems CDI Command-Data Interface CDF Common Data Format CDROM A data archival medium
Acronyms List (Page 1 of 8)
January 5, 2007 THEMIS Mission Readiness Review 200
Acronyms List (Page 2 of 8)
CESR Centre d’Etude Spatiale des Rayonnements CEI Contract End Item CEO Chief-Executive Officer CETP Centre d’etude des Environnements Terrestres et Planetaires, Velizy, France CGM Canadian Geospace Monitoring CG Center of Gravity CGS Canadian Geospace System CHIPS Cosmic Hot Interstellar Plasma Spectrometer (A NASA UNEX mission). CITU Carrier Initiator and Telemetry Unit CLCW Command Link Control Word CLTU Command Link Transmission Unit CLUSTERA European / US Scientific Satellite that was destroyed at launch CLUSTERIIA repeat of CLUSTER CM Contracts Managers CMD Command CMS Command Management System CNES Centre National d’Etudes Spatiales CNR Carrier-to-noise Ratio COP Command Operation Procedure CPMN Circum Pacific Magnetometer Network CPT Comprehensive Performance Testing CPU Central Processing Unit CQ Calendar Quarter CRRES An Airforce Mission (Combined Release and Radiation Effects Satellite) with Scientific Instruments CSA Canadian Space Agency CSR Concept Study Report
CU Colorado University CY Calendar Year DAC Digital-to-Analog Converter DAS Debris Assessment Software DC Direct Current DC MUX Direct Current Multiplexer DET Direct Energy Transfer DFB Digital Fields Board in the Instrument Data Processing Unit (IDPU) DLR German Aerospace Center DMA Direct Memory Access DMI Danish Meterological Institute DOD Depth of Discharge DPMB Data Processor & Memory Board DPU Data Processing Unit DSN Deep Space Network (A NASA tracking antenna network) DSP Data Signal Processor Dst A Geomagnetic Activity Index E&B Electric and Magnetic (Fields) EDAC Error Detection and Correction circuit EECO Electronic Engineering Change Order EFI Electric Field Instrument EFW Electric Field andWave experiment on CLUSTER, and CLUSTERII EGSE Electrical Ground Support Equipment EM Engineering Models EMC/EMI Electromagnetic Cleanliness/Electromagnetic Interference EO-1 Earth-Observing Satellite-1, a NASA mission
January 5, 2007 THEMIS Mission Readiness Review 201
Acronyms List (Page 3 of 8)
HST Hubble Space TelescopeHV High VoltageI&T Integration and TestingIAT Independent Assessment TeamICD Interface Control DocumentsIDL Interactive Data Language (a data analysiscommercial program)IDPU Instrument Data Processing UnitIGRF International Geophysical ReferenceModelIIRV Improved Interrange VectorIMAGE Imager for Magnetopause-to AuroraGlobal Exploration (MIDEX Mission)IMPACT The In-situ Measurements of Particlesand CME Transients investigation onSTEREO. This is a consortium ofseven instruments: The Solar Wind/SW, Magnetometer/MAG, Solar EnergeticParticle package/SEP composedof 4 smaller instruments. The IMPACTdata processing unit accomodates these7 instruments and additionally thePlasma and Supra-Thermal Ions andComposition/PLASTIC investigationon STEREO.IMU Inertial Measurement Unit (a commercialgyroscope)IMF Interplanetary Magnetic FieldInterball A Russian scientific satelliteI/O Input/Output
EPO Education and Public OutreachEquator-S A German Scientific SatelliteESA Electrostatic AnalyzerESC Electrostatic CleanlinessESTEC European Space Research and TechnologyCenterETU Engineering and Testing UnitEUVE Extreme Ultra-Violet ExplorerFAST Fast Auroral SnapshoT Explorer, aSMEX missionFDAB Flight Dynamics Analysis BranchFDC Flight Dynamics CenterFDF Flight Dynamics FacilityFEM Finite Element ModelFFT Fast Fourier TransferFGM Fluxgate MagnetometerFGS Fluxgate SensorFLT Flight-ready componentsFMEA Failure modes, and effects analysesFOT Flight Operations TeamFOV Field of ViewFPGA Field Programmable Gate ArrayFreja Swedish SatelliteFSW Flight SoftwareFTE Flux Transfer EventsFTP File Transfer ProtocolFUSE Far UltraViolet Spectroscopic ExplorerFUV Far UltraViolet (experiment onIMAGE mission)FY Fiscal YearGalileo NASA Satellite to Jupiter
HST Hubble Space TelescopeHV High VoltageI&T Integration and TestingIAT Independent Assessment TeamICD Interface Control DocumentsIDL Interactive Data Language (a data analysiscommercial program)IDPU Instrument Data Processing UnitIGRF International Geophysical ReferenceModelIIRV Improved Interrange VectorIMAGE Imager for Magnetopause-to AuroraGlobal Exploration (MIDEX Mission)IMPACT The In-situ Measurements of Particlesand CME Transients investigation onSTEREO. This is a consortium ofseven instruments: The Solar Wind/SW, Magnetometer/MAG, Solar EnergeticParticle package/SEP composedof 4 smaller instruments. The IMPACTdata processing unit accomodates these7 instruments and additionally thePlasma and Supra-Thermal Ions andComposition/PLASTIC investigationon STEREO.IMU Inertial Measurement Unit (a commercialgyroscope)IMF Interplanetary Magnetic FieldInterball A Russian scientific satelliteI/O Input/Output
EPO Education and Public OutreachEquator-S A German Scientific SatelliteESA Electrostatic AnalyzerESC Electrostatic CleanlinessESTEC European Space Research and TechnologyCenterETU Engineering and Testing UnitEUVE Extreme Ultra-Violet ExplorerFAST Fast Auroral SnapshoT Explorer, aSMEX missionFDAB Flight Dynamics Analysis BranchFDC Flight Dynamics CenterFDF Flight Dynamics FacilityFEM Finite Element ModelFFT Fast Fourier TransferFGM Fluxgate MagnetometerFGS Fluxgate SensorFLT Flight-ready componentsFMEA Failure modes, and effects analysesFOT Flight Operations TeamFOV Field of ViewFPGA Field Programmable Gate ArrayFreja Swedish SatelliteFSW Flight SoftwareFTE Flux Transfer EventsFTP File Transfer ProtocolFUSE Far UltraViolet Spectroscopic ExplorerFUV Far UltraViolet (experiment onIMAGE mission)FY Fiscal YearGalileo NASA Satellite to Jupiter
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Acronyms List (Page 4 of 8) IOC In Orbit Checkout IONet Internet Protocol Operational Network IPDR/ICDRInternal Preliminary and Critical Design Reviews IRM Spacecraft part of the AMPTE mission (also see AMPTE) IRT Independent Review Team ISDN Integrated Service Digital Network ISEE A NASA scientific satellite ISIS A US Polar Orbiting Satellite IT Information Technology ISTP International Solar-Terrestrial Program ISUAL Instrument built by UCB for a Taiwanese satellite ITAR International Traffic in Arms Regulations ITOS Integrated Test and Operation System IV&V Independent Verification and Validation IWF Institut für Weltraumforschung (Space Research Institute, Graz) IWS Integration Work Station JPL Jet Propulsion Laboratory KH Kelvin-Helmholtz KSC Kennedy Space Center L&EO Launch and Early Orbit LANL Los Alamos National Laboratory Landsat US Remote Sensing Satelllite LET Linear Energy Transfer (1 MeV cm2/g) LEO Low Earth Orbit LHS Lawrence Hall of Science LHCP Left Hand Circular Polarization
LME Lead Mechanical Engineer LOF Likelihood of Failure LPT Limited Performance Testing LV Launch Vehicle L/V also Launch Vehicle LVPS Low-Voltage Power Supply LWS Living With a Star program of NASA MACCS A Ground Magnetometer Network MAG MAGnetometers MagCon Magnetospheric Constellation a NASA mission under study, in the Solar Terrestrial Probes category MAM Mission Assurance Manager MCM-V Multi Chips Module Vertical MCP Micro-channel Plate MEASUREA ground magnetometer array along the Eastern United States MER Mars Exploration Rover MeV Mega (106) electron Volts MGS McMurdo Ground Station MHD Magnetohydrodynamics MIDEX Middle Explorer program of NASA MIR The Russian Space Station MI Magnetosphere-Ionosphere MLI Multi-layer Insulation MLT Magnetic Local Time MMS Magnetospheric Multiscale mission MO&DA Mission Operation and Data Analysis MOC Mission Operations Center MOM Mission Operations ManagerS MOSFET Metal-Oxide-Semiconductor Field- Effect Transistor
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Acronyms List (Page 5 of 8)
MOT Mission Operations Team MPS Mission Planning System MSASS Multimission Spin Axis Stabilized Spacecraft (MatLab-based GSFC code) MSE Mission Systems Engineer MSI&T Mission Integration and Testing (and Preparation for Operations as defined in this AO) N2H4 Monopropellant Hydrazine NASA National Aeronautics and Space Administration NENL Near-Earth Neutral Line model of substorms NIPR National Institute of Polar Research, Tokyo, Japan NLS NASA Launch Services NORAD North American Aerospace Defense Command NORSTARA Canadian program to instrument with filtered all sky imagers 6 ground stations NPD NASA Policy Directive NPG NASA Procedures and Guidelines NRC National Research Council NRE Non-Recurring Engineering NSES National Science Education Standards NSPAR Non-Standard Parts Approval Request NSSDC National Space Science Data Center NTIA National Telecommunications and Information Administration ODC Other Direct Changes OSS Office of Space Sciences
PA Product Assurance PAF Probe separation system PAIP Performance Assurance Implementation Plan PC Probe Carrier PCA Probe Carrier Assembly PESA-H PESA-High (an instrument on the WIND satellite) PFR Problem/Failure Reporting system Phobos A Russian Scientific Mission PI Principal Investigator Pi2 Pulsation irregular of type 2 PiB Pulsation irregular of type B PIL Parts Identification List PM Project Manager PM Phase Modulation PMC Program Management Council PMS Performance Measurement System POLAR A US Scientific Mission PPL Preferred Parts List PRA Probabilistic Risk Assessment PRIMAVERA Scheduling Software Package PROM Programmable Memory PSAT Predicted Site Acquisition Table PSR Program Status Reviews PTPNT Programmable Telemetry Processor for Windows NT QA Quality Assurance QUATRO QUantitative Assessment of Magnetospheric TRanspOrt RAID Redundant Array of Independent Disks
January 5, 2007 THEMIS Mission Readiness Review 204
Acronyms List (Page 6 of 8)
RAP Right Ascension of Perigee RAAN Right Ascension of the Ascending Node RE Mean Radius of Earth RHESSI Ramaty High Energy Solar Spectroscopic Imager RCS Reaction Control System RF Radio Frequency RFA Request for Action RFCS RF Comminations Subsystem RFQ Request for Quotations RHCP Right Hand Circular Polarization RID DSN station in MadRIT, Spain ROMAP A particle and field instrument on the European Rosetta Mission ROSETTA European Satellite RTS Relative Time Sequence Rx Reconnection site S3-3 An Airforce mission with scientific instruments to study the aurora SAC-C Brazilian satellite to be launched by NASA SACNAS Society for the Advancement of Chicanos and Native Americans in Science SAMBA A Ground Magnetometer Network SAMPEX Solar Anomalous and Magnetospheric Particle Explorer, A NASA Small Explorer mission SB Small Business SBUs Strategic Business Units SC Spacecraft
SCa Search Coil antennae SCpa Search Coil preamplifier unit SCAT Spacecraft Command and Telemetry SCAMA Switching, Conferencing and Monitoring Arrangement SCM Search Coil Magnetometer SCONCE A dispenser structure built for AFRL by Swales SDB Small Disadvantaged Business SDRAM Static/Dynamic Random Access Memory SDT Science Data Tool SEC Sun-Earth Connections SEGway Science Education Gateway, a UCBled education and public outreach program SEI-CMM Software Engineering Institute’s Capability Maturity Model. SEPT Solar Electron and Proton Telescope SERS Spacecraft Emergency Response System SEU Sudden Event Upset SMALL Sino-Magnetic Array at Low Latitudes (an NSF-funded effort) SMEX Small Explorer Program SMRB Swales Materials Review Board SN Space Network SOC Science Operations Center SOHO A US / European Scientific Satellite SOW Statement of Work SPB Spin-Plane Booms SPCB Swales Parts Control Board SPR Spare units SR&T Space Research and Technology program
January 5, 2007 THEMIS Mission Readiness Review 205
Acronyms List (Page 7 of 8)
of NASA SSD Space Sciences Division SSL Space Sciences Laboratory at UCB SSPA Solid State Power Amplifier SSS Swales Structure Systems SST Solid State Telescope SR System Reliability SRAM Static Random Access Memory SRO Systems Review Office STAFF A French experiment on the European satellite, CLUSTER STDN Spaceflight Tracking and Data Network STEM A production line of carbon epoxy tubular sensors STEREO A NASA Solar Terrestrial Probes mission to study the Sun from two spacecraft providing stereoscopic view of flares and coronal mass ejections ST5 A NASA technology demonstration mission STK Satellite Tool Kit STP Solar Terrestrial Probes STS/SHELS Shuttle Payload SWIFT US Mission TCP/IP Transmission Control Protocol/Internet Protocol TDRSS Tracking and Data Relay Satellite System, includes 6 spacecraft and ground centers for satellite communications TDRSS/MATDRSS Multiple Access mode THEMIS Time History of Events and Macroscale
Interactions during Substorms TIMED A NASA Scientific Satellite TLM Telemetry TRIANA NASA Mission to the L-1 Point TUBS Technical University, Braunschweig T/V Thermal Vacuum UA University of Alberta, Canada UC University of Calgary UCB University of California at Berkeley UCLA University of California at Los Angeles UC-LANLA Ground Magnetometer Network ULDB Ultra Long Duration Balloon ULF Ultra-low Frequency UNEX University Explorer UOSAT University of Surrey USAF US AirForce USN Universal Space Net, a commercial satellite tracking network. USN-AU Universal Space Network Australia USP University of Saint-Petersburg, Russia USGS U.S. Geological Survey UT Universal Time UTC Universal Coordinated TimeS UTDF Universal Tracking Data Format UV Ultra-Violet VSat Virtual Satellite VSAT A satellite internet connection Viking A Swedish Satellite VLSI Very Large Scale Integrated VME Virtual Memory Extension VRTX A Real Time Operating System commercial
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Acronyms List (Page 8 of 8)
program for microcontrollers WBS Work Breakdown Structure WGN Wallops Ground Network WGS Wallops Ground Station WGST White Sands Ground Terminal WIND An ISTP spacecraft to study the solar wind WOA Work Order Authorization WWW World-Wide Web